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EUROPEAN ORGANISATION
FOR THE SAFETY OF AIR NAVIGATION
EUROCONTROL
EUROCONTROL EXPERIMENTAL CENTRE
USER MANUAL FOR THE BASE OF AIRCRAFT DATA (BADA) REVISION 3.9
EEC Technical/Scientific Report No. 11/03/08-08
Project BADA
Public
Issued: April 2011
© European Organisation for the Safety of Air Navigation EUROCONTROL 2007
This document is published by EUROCONTROL in the interest of the exchange of information. It may be copied in whole or in part
providing that the copyright notice and disclaimer are included. The information contained in this document may not be modified without
prior written permission from EUROCONTROL.
EUROCONTROL makes no warranty, either implied or express, for the information contained in this document, neither does it assume
any legal liability or responsibility for the accuracy, completeness or usefulness of this information.
REPORT DOCUMENTATION PAGE
Reference
EEC Technical/Scientific Report
No. 11/03/08-08
Security Classification
Unclassified
Originator:
DSR/CMN/VIF
Originator (Corporate Author) Name/Location:
EUROCONTROL Experimental Centre
Centre de Bois des Bordes
B.P.15
F - 91222 Brétigny-sur-Orge CEDEX
FRANCE
Telephone: +33 (0)1 69 88 75 00
Internet : www.eurocontrol.int
Sponsor:
EUROCONTROL
Sponsor (Contract Authority) Name/Location
EUROCONTROL Agency
Rue de la Fusée, 96
B -1130 BRUXELLES
Telephone: +32 (0)2 729 9011
Internet : www.eurocontrol.int
TITLE:
USER MANUAL FOR THE BASE OF Aircraft DATA (BADA) REVISION 3.9
Author
Date
Pages
Figures
Tables
Annexes
References
A. Nuic
04/11
xviii + 88
0
2
2
15
Project
Task no. sponsor
Period
BADA
DSR/CMN/VIF
04/10 to 04/11
Distribution Statement:
(a) Controlled by: Head of section
(b) Distribution : Public
Restricted
(c) Copy to NTIS: YES / NO
Confidential
Descriptors (keywords) :
Aircraft model, total-energy model, BADA, user manual.
Abstract :
The Base of Aircraft Data (BADA) provides a set of ASCII files containing performance and operating
procedure coefficients for 338 different aircraft types. The coefficients include those used to calculate
thrust, drag and fuel flow and those used to specify nominal cruise, climb and descent speeds. User
Manual for Revision 3.9 of BADA provides definitions of each of the coefficients and then explains the file
formats. Instructions for remotely accessing the files via Internet are also given.
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User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
SUMMARY
The Base of Aircraft Data (BADA) provides a set of ASCII files containing performance and
operating procedure coefficients for 338 different aircraft types. The coefficients include those used
to calculate thrust, drag and fuel flow and those used to specify nominal cruise, climb and descent
speeds. The User Manual for Revision 3.9 of BADA provides definitions of each of the coefficients
and then explains the file formats. Instructions for remotely accessing the files via Internet are also
given.
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
v
EUROCONTROL
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
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Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
USER MANUAL MODIFICATION HISTORY
Issue Number
Release Date
Comments
Revision 2.1
Issue 1.0
31.05.94
First release of document
Revision 2.2
25.01.95
Released with BADA Revision 2.2
Issue 1.0
- 8 new aircraft models
- 2 modified aircraft models
- 2 modified equivalences
- 6 removed equivalences
- 14 new equivalences
- modified file formats
- additional Synonym File
- corrections to formulas in previous version of
document
- additional description of total-energy and
standard atmosphere equations
Revision 2.3
Issue 1.0
08.06.95
Released with BADA Revision 2.3
- document format modified to be consistent with
EEC Technical Note standards
- new A/C models for B73V and D328
- MD11 changed from equivalence to direct support
- generic military fighter model, FGTR, replaces
specific fighter models
- maximum payload parameter added to
all OPF files
- Performance Tables Files (*.PTF) introduced
- ISA equations used for TAS/CAS conversions
instead of approximations (Section 3.2)
- use only one formula for correction of speeds
at mass values different from reference mass
(Section 3.3)
- add specification of minimum speed as function
of stall speed (Section 3.4)
- specification of transition altitude calculated added
(Section 4.1)
- speed schedules modified for climb (Section 4.1)
and descent (Section 4.3)
- modify Internet address for remote access and
EUROCONTROL contact person (Section 6)
- removed Section 7 (General Comments)
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
vii
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
Issue Number
Revision 2.4
Issue 1.0
Release Date
04.01.96
Comments
Released with BADA Revision 2.4
- new A/C model for FK70
- C421 changed from equivalence to directly supported
- 10 new equivalences
- 1 modified equivalence
- 3 re-developed models
- introduction of dynamic maximum altitude
- new temperature correction on thrust
- modified max.alt for 4 models
- modified minimum weight for 2 models
- modified temperature coefficients for 12 models
- esf calculation for constant CAS below tropopause
changed from binomial approximation to exact formula
- cruise Mach numbers changed for 4 models
- change in altitude limit for descent speed
Revision 2.5
Issue 1.0
20.01.97
- re-developed models: EA32, B737, B73S, AT42, B767,
DC9, BA46, FK10, MD80.
- new model: CL65, DH83
- change of minimum speeds
- change of climb/descent speed schedules
- cruise fuel flow correction
- buffeting speed for jet a/c
- addition of BADA.GPF file
- definition of acceleration limits, bank angles and holding
speeds
- 38 new equivalences added (SA4, SA5, SweDen 96)
- 1 modified equivalence (B74S)
- modified climb/cruise speeds (BE90, BE99, E120,
PA42, FK50, B73F, B767,B747, B727, DA20)
- Format changes in OPF file
- Header changes in PTF file
- Temperature influence on thrust limitation changed
- Unit of Vstall in OPF file changed to KCAS
- Correction of typing errors
- Correction of APF file format explanation
Revision 2.6
Issue 1.0
viii
01.09.97
- Added non-clean drag and thrust data for: EA32, B73S,
MD80, B737, B747, FK10, AT42, B767 and CL65
models
- All models mentioned above were re-developed using
new clean drag data.
- ND16, E120 and FK50 were re-modelled to correct the
cruise speed capability.
- Change of speed schedule in the take-off / initial climb
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
Issue Number
Release Date
EUROCONTROL
Comments
phase and approach / landing phase
- Change in descent thrust algorithm
- Use of exact formula for density below tropopause
instead of approximation.
- Addition of formula for pressure above tropopause
- Change of buffeting limit to 1.2g (was 1.3g)
- Change of OPF file format
- Buffeting coefficients for B757 and MD80 were
corrected.
- Hmo for B747 model was corrected to 45,000 ft
- Low altitude descent behaviour corrected for: SW3,
PAYE, DA50, DA10, D328, C421, BE99, BE20 and
BE90 models
- Correction of some minor typing errors
- dynamic maximum altitude coefficients changed for
B747, B74F, C130 and EA30
- Saab 2000 (SB20) added as equivalent of D328
- Modified algorithm for lift coefficient
Revision 3.0
Issue 1.0
01.03.98
- Climb speed law changed for jet aircraft
- Descent speed law changed for jet, turbo and piston
- Reduced power climbs
- B777, SB20 and B73X models were added
- DA01 model was removed
- Use of ICAO doc. 8643/25 standard, which resulted in
the removal of 4 additional models
- B73F and B757 remodelled
- MD90 added as equivalence model
- Cruise and descent speeds for several turboprops
changed
- Climb thrust for several a/c changed
- Removal of Cm16 from drag expression
Revision 3.1
Issue 1.0
01.10.98
Released with BADA Revision 3.1
- Descent & cruise speeds for several jet aircraft
changed: DC9, BA46, CL60
- Descent, cruise & climb speeds for several turboprops
changed: D228, SH36
- Maximum Operating speed for several a/c changed:
PA42
- Stalling speed for several a/c changed : DC8, T154
- Removed formula for air density calculation above
tropopause
- Addition of Appendix D : Solutions for buffeting limit
algorithm
- Removed Section 3.7.2 : Maximum Take-Off Thrust
- Description for Cred parameter added
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
ix
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
Issue Number
Release Date
Comments
- Correction of some minor typing errors
- Modified PTF File format (Flight Level): Section 6.6
- Cruise CAS schedule for jet & turbo aircraft (Section
4.2)
Released with BADA Revision 3.3
- Standard atmosphere explanation added
- Correction of some typing errors, minor changes in
the layout and equations presentation.
- Several aircraft types have changed ICAO’s
designator according to the ICAO doc.8643/27.
Aircraft types affected by the RD3 are as follows:
A300, ATR, B707, B727, B73A, B73B, B73C, B74A,
B74B, B757, B767, B777, CARJ, DC8, DHC8, JSTA,
JSTB, P31T, PA28, PA42. That resulted in:
modification of the name of the OPF and APF files,
addition of new models as synonyms, modification of
Synonym.NEW and Synonym.LST files.
- B73A, B757, MD80, B73B, F100, B727, CARJ, FA20,
FA50, D228, T154 aircraft models have been remodelled
- A319, A321, A306, AT72 models have been added
- Climb, cruise and descent speeds changed for
several models.
- Ground TOL for B73C has been modified.
MD80: Cd0 and Cd2 for IC and TO added, maximum
altitude at MTOW, ISA weight gradient on maximum
altitude Gw and temperature gradient Gt on
maximum altitude have been changed
- BA46 maximum altitude at MTOW, ISA weight
gradient on maximum altitude Gw have been
changed
- E145 was added as equivalent of CRJ1
Revision 3.3
Issue 1.0
-
Revision 3.4
Issue 1.0
x
June 2002
A478 was added as equivalent of AT72
Released with BADA Revision 3.4
- correction of some typing errors
- in chapter 3.5 configuration threshold altitude values
replaced with Hmax,i while the corresponding numbers
are listed in chapter 5.6
- Appendix B: a new column is added to the table;
providing the information on maximum altitude that
an aircraft can reach at MTOW (hmax)
- FGTN aircraft model added
-
FGTH aircraft model added
-
FGTL aircraft model added
-
FGTR aircraft model removed
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
Issue Number
Revision 3.5
Issue 1.0
Release Date
July 2003
EUROCONTROL
Comments
-
DC-9 aircraft model re-modelled
-
D228 cruise and descent speed modified
-
SH36 cruise and descent speed modified
-
B738 maximum operational altitude modified
-
AT72 cruise speed corrected
-
PA34 minimum mass modified
-
B734 aircraft model added
-
B735 aircraft model added
-
E145 aircraft model added
-
B737 aircraft model added
-
AT45 aircraft model added
-
B762 aircraft model added
-
B743 aircraft model added
-
Removal of several existing OPF and APF files due
to the change of ICAO aircraft designators according
to RD3: A330, A340, BA46, DC9, MD80
-
Addition of several new OPF and APF files due to the
change of ICAO aircraft designators according to
RD3: A333, A343, B461, DC94, MD83
-
Addition of new equivalence aircraft types: A332,
A342, A345, A346, B461, B462, B463, DC91, DC92,
DC93, DC95, MD81, MD82, MD87, MD88, A124,
AC80, AC90, AC95, AJET, AMX, AN72, ATLA, B1,
B350, B739, B74D, BDOG, BE10, BE40, BE76,
BER4, C17, C72R, C77R, C82R, C210, C212, C337,
C526, C56X, CRJ7, E135, EUFI, F1, FT2H, F104,
G222, GLF5, HAWK, H25A, H25C, IL96, JS1, JS3,
JS20, LJ24, M20T, M20P, K35R, N262, P28T, P28B,
PA32, PAY4, P68, PA44, SB05, T204, TBM7
-
Modification of the value for Maximum bank angles
for civil flight during HOLD in BADA.GPF file
-
Configuration Management of BADA files have been
changed; files have been migrated from RCS to
Continuus Configuration Management System. That
resulted in the modification of the “identification” part
of all BADA files given in the header.
Released with BADA Revision 3.5
- correction of some typing errors
-
B712 aircraft model added
-
LJ45 aircraft model added
-
C750 aircraft model added
-
RJ85 aircraft model added
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
xi
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
Issue Number
Revision 3.6
Issue 1.0
Release Date
July 2004
Comments
-
B736 aircraft model added
-
B753 aircraft model added
-
A332 aircraft model added
-
B772 re-modelled
-
B738 re-modelled
-
B763 re-modelled
-
B703 WTC modified
-
JS41 WTC modified
-
Addition of new syn. aircraft types: P180, GLEX,
C30J, J328, A7, B52, ETAR, F117, L159
-
Modification of BADA models for existing
synonym aircraft types: C17, GLF3, GLF3, GLF4,
GLF5
-
SYNONYM_ALL.LST file added.
Released with BADA Revision 3.6
The following models of aircraft added in BADA 3.6:
- Dash 8-100: DH8A
- Boeing MD82: MD82
- Boeing B767-400: B764
- Boeing B777-300: B773
- BAE 146-200: B462
The following models of aircraft have been re-modelled in
BADA 3.6:
- Airbus A300B4-203: A30B
- Airbus A310: A310
- Airbus A319: A319
- Airbus A320: A320
- Airbus A321: A321
- Airbus A330-301: A333
- Airbus A340-313: A343
- Boeing B737-200: B732
- Boeing B737-300: B733
- Boeing B747-200: B742
- Boeing B747-400: B744
- Boeing B757-200: B752
Addition of new synonym aircraft types:
A3ST, ASTR, B701, C441, GALX, J728, K35A, K35E,
L29B, LJ25, LJ60, NIM, PC12, R135, RJ1H, RJ70, P32R,
C208, AA5, S76, DC3, BLAS, AEST, EC35, PAY1, PA18,
BE55, C170, B461.
Correction of syntax errors in BADA files:
xii
-
Boeing B777-200: B772
-
ATR42-500: AT45
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
Issue Number
Revision 3.7
Release Date
Comments
March 2009
Released with BADA Revision 3.7
- Modification of the values for constants g and R
in Section 3.
- New description of formula 3.1-8 to match its
actual use in some models.
- Coefficient CVmin, TO is no longer used in climb
speed schedule, only in flight envelope
determination.
- Numbering of several equations changed due to
reorganisation of related sections.
- Change of descent thrust computation when
CTdes,app and CTdes, ld are null in Section
3.7.3.
- Clarification of descent fuel flow computation in
Section 3.9.
- Additional information on climb and descent
speed schedules in Section 4.
- Update of some Fortran format descriptions in
Section 6.
- Additional reasons for ROCD discontinuities
added in Section 6.6.
- Introduction of new PTD file format.
- Update of Section 7 to describe the new means
of access to the BADA files.
- Remodelling of 71 a/c types from BADA 3.6 more details in [RD8].
- Addition of 12 new a/c models for following a/c
types: A346, A388, BE58, C510, CRJ2, CRJ9,
DA42, DH8D, E135, E170, E190, EA50.
- All synonym aircraft have been re-evaluated and
some reassigned – more details in [RD12]
reassigned.
-
Issue 1.0
Revision 3.8
Issue 1.0
EUROCONTROL
April 2010
Released with BADA Revision 3.8
-
Introduction of new revised atmosphere model
and relevant corresponding updates throughout
the User Manual document
-
Harmonisation of acronyms for physical
constants with the EEC Technical Report No.
2010-001, February 2010 “Revision of
Atmosphere
Model
in
BADA
Aircraft
Performance Model”
-
Clarification of descent fuel flow computation in
Section 3.9.
-
Information added on whether some BADA
model coefficients may or may not be negative.
-
Missing information about speed schedule in
cruise for piston aircraft added (section 4.2)
-
Additional clarifications provided on use of
altitudes in Section 4.
-
Additional explanatory note provided on data
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
xiii
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
Issue Number
Release Date
Comments
presented in the PTF file.
-
Correction of error in the solution for buffeting
limit algorithm.
-
Remodelling of 5 a/c types from BADA 3.7:
B763, FA50, F900, RJ85, TRIN
-
Addition of 8 new a/c models :
A318, A3ST, A345, B739, B77L, B77W,
F2TH, FA7X.
Revision 3.8
August 2010
Issue 1.1
-
23 new synonym aircraft added – more details in
[RD12].
-
Regeneration of all PTF/PTD files
Clarifications only, no impact on BADA implementations:
- Overall review of the document to fix formatting and
typography problems.
- Formula 3.1-19 (approximate value of a constant)
removed, formula 3.1-4 added to define TISA,trop, and
some formulas reordered in section 3.1
Revision 3.9
Issue 1.0
April 2011
Released with BADA Revision 3.9 (more details in [RD8
and RD12]):
-
Minor updates in the document
-
Clarification about speed calculation in Chapter
4.2. Cruise
-
Remodelling of 4 a/c types from BADA 3.8:
A320, BE58, DA42, E135
-
Addition of 6 new a/c models :
AT72, AT75, C56X, E50P, E55P,TBM7
-
xiv
17 new synonym aircraft added and 13 existing
synonyms have been revised
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
TABLE OF CONTENTS
SUMMARY ......................................................................................................................... V
USER MANUAL MODIFICATION HISTORY ................................................................... VII
1. INTRODUCTION ...........................................................................................................1
1.1.
IDENTIFICATION ......................................................................................................... 1
1.2.
PURPOSE .................................................................................................................... 1
1.3.
DOCUMENT ORGANISATION..................................................................................... 1
1.4.
REFERENCED DOCUMENTS ..................................................................................... 2
1.5.
GLOSSARY OF ACRONYMS....................................................................................... 3
1.6.
GLOSSARY OF SYMBOLS.......................................................................................... 4
2. REVISION SUMMARY..................................................................................................5
2.1.
SUPPORTED AIRCRAFT............................................................................................. 5
2.2.
UPDATES FOR BADA REVISION 3.9.......................................................................... 5
3. OPERATIONS PERFORMANCE MODEL....................................................................7
3.1.
ATMOSPHERE MODEL ............................................................................................... 7
3.1.1. Definitions ....................................................................................................... 7
3.1.2. Expressions .................................................................................................... 8
3.2.
TOTAL-ENERGY MODEL .......................................................................................... 13
3.3.
AIRCRAFT TYPE ....................................................................................................... 17
3.4.
MASS ......................................................................................................................... 17
3.5.
FLIGHT ENVELOPE................................................................................................... 18
3.6.
AERODYNAMICS....................................................................................................... 20
3.6.1. Aerodynamic Drag ........................................................................................ 20
3.6.2. Low Speed Buffeting Limit (jet aircraft only) .................................................. 21
3.7.
ENGINE THRUST ...................................................................................................... 22
3.7.1. Maximum Climb and Take-Off Thrust............................................................ 22
3.7.2. Maximum Cruise Thrust ................................................................................ 23
3.7.3. Descent Thrust.............................................................................................. 23
3.8.
REDUCED CLIMB POWER........................................................................................ 24
3.9.
FUEL CONSUMPTION............................................................................................... 25
3.9.1. Jet and Turboprop Engines ........................................................................... 25
3.9.2. Piston Engines .............................................................................................. 26
3.10. GROUND MOVEMENT .............................................................................................. 26
3.11. SUMMARY OF OPERATIONS PERFORMANCE PARAMETERS.............................. 27
4. AIRLINE PROCEDURE MODELS ..............................................................................29
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
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User Manual for the Base of Aircraft Data (BADA) Revision 3.9
4.1.
CLIMB ........................................................................................................................ 30
4.2.
CRUISE ...................................................................................................................... 31
4.3.
DESCENT .................................................................................................................. 32
5. GLOBAL AIRCRAFT PARAMETERS ........................................................................33
5.1.
INTRODUCTION ........................................................................................................ 33
5.2.
MAXIMUM ACCELERATION...................................................................................... 33
5.3.
BANK ANGLES .......................................................................................................... 34
5.4.
EXPEDITED DESCENT ............................................................................................. 34
5.5.
THRUST FACTORS ................................................................................................... 34
5.6.
CONFIGURATION ALTITUDE THRESHOLD ............................................................. 35
5.7.
MINIMUM SPEED COEFFICIENTS............................................................................ 35
5.8.
SPEED SCHEDULES................................................................................................. 35
5.9.
HOLDING SPEEDS .................................................................................................... 36
5.10. GROUND SPEEDS .................................................................................................... 36
5.11. REDUCED POWER COEFFICIENT ........................................................................... 36
6. FILE STRUCTURE......................................................................................................37
xvi
6.1.
FILE TYPES ............................................................................................................... 37
6.2.
FILE CONFIGURATION MANAGEMENT ................................................................... 38
6.2.1. File Identification ........................................................................................... 39
6.2.2. History........................................................................................................... 40
6.2.3. Release......................................................................................................... 40
6.2.4. Release Summary file ................................................................................... 40
6.3.
SYNONYM FILE FORMAT ......................................................................................... 41
6.3.1. SYNONYM.LST File...................................................................................... 41
6.3.2. SYNONYM.NEW File.................................................................................... 43
6.3.3. SYNONYM_ALL.LST File ............................................................................. 46
6.4.
OPF FILE FORMAT.................................................................................................... 49
6.4.1. File Identification Block ................................................................................. 50
6.4.2. Aircraft Type Block ........................................................................................ 50
6.4.3. Mass Block.................................................................................................... 51
6.4.4. Flight Envelope Block.................................................................................... 51
6.4.5. Aerodynamics Block...................................................................................... 52
6.4.6. Engine Thrust Block ...................................................................................... 53
6.4.7. Fuel Consumption Block ............................................................................... 54
6.4.8. Ground Movement Block............................................................................... 55
6.5.
APF FILE FORMAT .................................................................................................... 55
6.5.1. File Identification Block ................................................................................. 56
6.5.2. Procedures Specification Block ..................................................................... 56
6.6.
PTF FILE FORMAT .................................................................................................... 58
6.7.
PTD FILE FORMAT.................................................................................................... 61
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
6.8.
EUROCONTROL
BADA.GPF FILE FORMAT ......................................................................................... 63
6.8.1. File Identification Block ................................................................................. 65
6.8.2. Class Block ................................................................................................... 65
6.8.3. Parameter Block ........................................................................................... 66
7. REMOTE FILE ACCESS ............................................................................................67
LIST OF APPENDICES
APPENDIX A BADA 3.9 – LIST OF AVAILABLE AIRCRAFT MODELS ........................69
APPENDIX B SOLUTIONS FOR BUFFETING LIMIT ALGORITHM ...............................86
LIST OF TABLES
Table 3-1: BADA Operations Performance Parameter Summary .................................................. 27
Table 7-1: List of Aircraft Types Supported by BADA 3.9 .............................................................. 71
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
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Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
1.
EUROCONTROL
INTRODUCTION
1.1. IDENTIFICATION
This document is the User Manual for the Base of Aircraft Data (BADA) Revision 3.9. This manual
replaces the previous User Manual for BADA Revision 3.8 [RD1].
1.2. PURPOSE
BADA is a collection of ASCII files which specifies operation performance parameters, airline
procedure parameters and performance summary tables for 338 aircraft types. This information is
designed for use in trajectory simulation and prediction algorithms within the domain of Air Traffic
Management (ATM). All files are maintained within a configuration management system at the
EUROCONTROL Validation Infrastructure Centre of Expertise located at the EUROCONTROL
Experimental Centre (EEC) in Brétigny-sur-Orge, France.
This document describes the mathematical models on which the data is based and specifies the
format of the files which contain the data. In addition, this document describes how the files can be
remotely accessed.
1.3. DOCUMENT ORGANISATION
This document consists of seven sections including Section 1, the Introduction. A list of referenced
documents along with a glossary of acronyms and symbols are included in this section.
Section 2: Revision Summary, summarises the differences between BADA 3.9 and the previous
revision BADA 3.8.
Section 3: Operation Performance Models, defines the set of equations, which are used to
parameterise aircraft performance. This includes models of aerodynamic drag, engine
thrust, and fuel consumption. An atmosphere model is also provided.
Section 4: Airline Procedure Models, defines the set of parameters which is used to characterise
standard airline speed procedures for climb, cruise, and descent.
Section 5: Global Aircraft Parameters, defines the set of global aircraft parameters that are valid
for all, or a group of, aircraft.
Section 6: File Structure, describes the files in which the BADA aircraft parameters are
maintained. Six types of files are identified:
• Synonym Files listing the supported aircraft types;
• Operations Performance Files (OPF) containing the performance parameters for a
specific aircraft type;
• Airline Procedures Files (APF) containing speed procedure parameters for a specific
aircraft type;
• Performance Table Files (PTF) containing summary performance tables of true
airspeed, climb/descent rates and fuel consumption at various flight levels for a
specific aircraft type;
• Performance Table Data (PTD) containing detailed performance data at various
flight levels for a specific aircraft type;
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• Global Parameters File (GPF) containing parameters that are valid for all aircraft or
a group of aircraft, for instance all turboprops or all military aircraft.
Section 7: Remote File Access to BADA, provides instructions on how to remotely access BADA
files from the EUROCONTROL computing facilities over the Internet.
Two appendices are also provided with this document. Appendix A provides a list of the aircraft
types supported by BADA 3.9 and Appendix B gives solutions for a buffeting limit algorithm.
1.4. REFERENCED DOCUMENTS
RD1
User Manual for the Base of Aircraft Data (BADA) Revision 3.8; EEC
Technical/Scientific Report No. 2010-003, April 2010.
RD2
Aircraft Type Designators, ICAO
http://www.icao.int/anb/ais/8643/
RD3
Aircraft Modelling Standards for Future ATC Systems; EUROCONTROL Division E1
Document No. 872003, July 1987.
RD4
Manual of the ICAO Standard Atmosphere; ICAO Document No. 7488, 2nd Edition,
1964.
RD5
BADA Product Management Document; EEC Technical Report No. 2009-008, April
2009.
RD6
Base of Aircraft Data (BADA) Aircraft Performance Modelling Manual: EEC
Technical Report No. 2009-009, April 2009.
RD7
Memo on the Calculation of Energy Share Factor; EEC/FAS/BYR/95/50; 22
November 1995.
RD8
Revision Summary Document for the Base of Aircraft Data (BADA) Revision 3.9;
EEC Technical/Scientific Report No. 11/03/08-09; April 2011.
RD9
Aircraft Performance Summary Tables for the Base of Aircraft Data (BADA)
Revision 3.9; EEC Technical/Scientific Report No. 11/03/08-10; April 2011.
RD10
Aircraft Type Designators, ICAO Document 8643, Version 24-39.
RD11
BADA Support Application – User Guide, revision 1.1, August 2009.
RD12
Synonym Aircraft Report for the Base of Aircraft Data (BADA) - Revision 3.9: EEC
Technical/Scientific Report No. 11/03/08-12, April 2011.
RD13
Model Accuracy Summary Report for the Base of Aircraft Data (BADA) - Revision
3.9: EEC Technical/Scientific Report No. 11/03/08-11, April 2011.
RD14
Revision of Atmosphere Model in BADA Aircraft Performance Model: EEC
Technical Report No. 2010-001, February 2010.
RD15
Mathematical Handbook; M.R. Spiegel; 1968; McGraw-Hill book company.
2
Document
8643/39,
2011
edition,
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1.5. GLOSSARY OF ACRONYMS
AGL
Above Ground Level
APF
Airlines Procedures File
ASCII
American Standard Code for the Interchange of Information
ATM
Air Traffic Management
BADA
Base of Aircraft Data
CAS
Calibrated Airspeed
EEC
EUROCONTROL Experimental Centre
ESF
Energy Share Factor
ICAO
International Civil Aviation Organisation
ISA
International Standard Atmosphere
MLW
Maximum Landing Weight
MSL
Mean Sea Level
MTOW
Maximum Take-off Weight
OPF
Operations Performance File
PTD
Performance Table Data
PTF
Performance Table File
RCS
Revision Control System
ROCD
Rate of Climb or Descent
TAS
True Airspeed
TEM
Total-Energy Model
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1.6. GLOSSARY OF SYMBOLS
A list of the symbols used in equations throughout this document is given below along with a
description. Where appropriate, the engineering units typically associated with the symbol are also
given.
a
speed of sound
[m/s]
d
distance
[nautical miles]
f
fuel flow
[kg/min]
g0
gravitational acceleration
[m/s2]
dh
dt
vertical speed
[m/s] or [ft/min]
h
geodedic altitude
[metres] or [ft]
H
geopotential altitude
[metres] or [ft]
Hp
geopotential pressure altitude
[metres] or [ft]
C
general coefficient
D
drag force
[Newtons]
m
aircraft mass
[tonnes] or [kg]
M
Mach number
p
Actual pressure
[Pa]
p0
Standard pressure at MSL
[Pa]
R
real gas constant for air
[m2/(K·s2)]
ROCD
Rate of Climb or Descent
[m/s] or [ft/min]
S
reference wing surface area
[m2]
T
temperature
[Kelvin]
Thr
thrust
[N]
V
speed
[m/s] or [knots]
∆T
temperature difference
[Kelvin]
W
weight
[N]
η
thrust specific fuel flow
[kg/(min·kN)]
ρ
air density
[kg/m3]
4
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2. REVISION SUMMARY
This section summarises the aircraft types that are supported in BADA Revision 3.9 along with the
updates that have been made from the previous release, BADA Revision 3.8.
2.1. SUPPORTED AIRCRAFT
BADA 3.9 provides operations and procedures data for a total of 338 aircraft types. For 117 of
these aircraft types, data is provided directly in files. These aircraft types are referred to as being
directly supported and referred to as aircraft original models. The way they have been identified is
described in [RD6]. For the other 221 aircraft types, the data is specified to be the same as one of
the directly supported 117 aircraft types. These aircraft types have been identified as being
‘equivalent’ to original aircraft models. They are referred to as synonym aircraft. More details on
the way they have been identified are given in [RD12].
With three exceptions, each supported aircraft type is identified by a 4-character designation code
assigned by the International Civil Aviation Organisation (ICAO) [RD2]. The exceptions are the
models representing generic military fighters, which use the designators: FGTH, FGTL, FGTN.
The list of aircraft types supported by BADA 3.9 is given in Appendix A. In this Appendix the
supported aircraft types are listed alphabetically by their designation code. For each aircraft type,
the aircraft name and type of BADA support (either original or synonym) is specified. Also, for each
synonym aircraft, which is supported through equivalence, the corresponding equivalent aircraft
type is specified.
2.2. UPDATES FOR BADA REVISION 3.9
Updates made to BADA Revision 3.9 from the previous revision 3.8 are listed below:
(a) Updates of existing documentation.
(b) Re-modelling of 4 aircraft models.
(c) Addition of 6 new aircraft models.
(d) Addition of new synonym aircraft.
(e) Implementation of new ICAO aircraft designators according to the ICAO doc. 8643 [RD2].
A more complete overview of all changes can be found in [RD8].
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3. OPERATIONS PERFORMANCE MODEL
This section defines the various equations and coefficients used by the BADA operations
performance model.
The first two subsections describe the equations for atmospheric properties and the Total-Energy
Model (TEM) equations respectively.
The remaining eight subsections define the aircraft model in terms of the eight categories listed
below:
•
•
•
•
•
•
•
•
aircraft type,
mass,
flight envelope,
aerodynamics,
engine thrust,
reduced power,
fuel consumption,
ground movement.
3.1. ATMOSPHERE MODEL
This section provides expressions for the atmospheric properties (pressure, temperature, density
and speed of sound) as a function of altitude which are required for calculation of aircraft
performances and movements1. Conversions from CAS to TAS and Mach number also require the
determination of several atmospheric properties as a function of altitude.
The most important equations for atmospheric properties used by BADA and CAS/TAS conversion
are summarised in this chapter, while other expressions and more details are provided in [RD14].
3.1.1. Definitions
Mean Sea Level (MSL) Standard atmosphere conditions are those that occur in the
International Standard Atmosphere (ISA) at the point where the geopotential pressure
altitude Hp2 is zero. They are denoted as T0, p0, ρ0 and a0 with the values listed below:
Standard atmospheric temperature at MSL :
T0
=
288.15
[K]
Standard atmospheric pressure at MSL :
p0
=
101325
[Pa]
Standard atmospheric density at MSL :
ρ0
=
1.225
[kg/m3]
Speed of sound :
a0
=
340.294
[m/s]
1 These equations are based on the International Standard Atmosphere (ISA) [RD4].
2 Geopotential pressure altitude Hp is the geopotential altitude H that occurs in the ISA atmospheric conditions [RD14].
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Mean Sea Level (MSL) atmosphere conditions are those that occur in a non-ISA
atmosphere. They are identified by the sub-index MSL and differ from (T0, p0, ρ0, a0) in nonISA conditions.
Non-ISA atmospheres are those that follow the same hypotheses as the ISA atmosphere
but differ from it in that one or both of the following parameters is not zero:
1. ∆T. Temperature differential at MSL. It is the difference in atmospheric temperature
at MSL between a given non-standard atmosphere and ISA.
2. ∆p. Pressure differential at MSL. It is the difference in atmospheric pressure at MSL
between a given non-standard atmosphere and ISA.
The values of these two parameters uniquely identify any non-ISA atmosphere. Thus, a
non-ISA atmosphere provides expressions for the atmospheric pressure, temperature and
density as functions of the geopotential altitude H3 and its two differentials. [RD14] provides
more details on the corresponding analytical expressions.
3.1.2. Expressions
The relationships linking the atmospheric pressure p, temperature T, geopotential pressure
altitude Hp and geopotential altitude H for any ISA4 and non-ISA atmosphere are provided
below.
Physical constants which are used throughout this chapter are listed below:
Adiabatic index of air :
κ
=
1.4
Real gas constant for air :
R
=
287.05287 [m2/(K·s2)]
Gravitational acceleration :
g0
=
9.80665
[m/s2]
ISA temperature gradient with altitude
below the tropopause :
βT,<
- 0.0065
[K/m]
=
Note that subindex < denotes values below and at the tropopause and subindex > denotes
values above the tropopause (as defined by 3.1-11).
Standard Mean Sea Level (subindex Hp = 0)
The temperature differential ∆T sets the value of the real temperature T in non-standard
atmospheres.
Hp,Hp=0 = 0
(3.1-1)
3 Geopotential altitude H is that which under the standard constant gravitational field provides the same differential work performed by
the standard acceleration of free fall when displacing the unit of mass a distance dH along the line of force, as that performed by the
geopotential acceleration when displacing the unit of mass a geodetic distance dh [RD14].
4 By replacing ∆T and ∆p parameters with zeros the expressions are made applicable to the case of the standard atmosphere.
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pHp=0 = p0
(3.1-2)
TISA,Hp=0 = T0
(3.1-3)
THp=0 = T0 + ∆T
(3.1-4)
HHp=0 =
T0
1
T0 − TISA,MSL + ∆T ⋅ Ln
β T,<
TISA,MSL
(3.1-5)
where TISA is the standard atmospheric temperature that occurs in the ISA atmosphere. It is
a function of the geopotential pressure altitude Hp.
Mean Sea Level (subindex MSL)
The pressure differential ∆p sets the value of the atmospheric pressure p.
HMSL=0
(3.1-6)5
pMSL = p0 + ∆p
(3.1-7)
Hp, MSL
T
= 0
β T,<
p MSL
p
0
−
βT, <R
g0
− 1
(3.1-8)
TISA,MSL = T0 + βT,< Hp,MSL
(3.1-9)
TMSL = T0 + ∆T + βT,< Hp,MSL
(3.1-10)
Tropopause
Tropopause is the separation between two different layers: the troposphere, which stands
below it, and the stratosphere, which is placed above. Its altitude Hp,trop is constant when
expressed in terms of geopotential pressure altitude:
Hp,trop = 11000 [m]
(3.1-11)
5 In order to simplify the expressions, this document assumes that the geopotential altitude at mean sea level is always zero.
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a)
b)
Determination of Temperature
T = f (Hp, ∆T)
(3.1-12)
T< = T0 + ∆T + βT,< Hp,<
(3.1-13)
TISA,trop = T0 + βT,< Hp,trop
(3.1-14)
Ttrop = T0 + ∆T + βT,< Hp,trop
(3.1-15)
T> = Ttrop
(3.1-16)
Determination of Air Pressure
p = f (T, ∆T)
T − ∆T
p < = p 0 <
T0
(3.1-17)
−
g0
βT, < R
Ttrop − ∆T
p trop = p 0
T0
−
(3.1-18)
g0
βT, < R
(3.1-19)
T> = Ttrop, so p> does not directly depend on temperature T>. For altitudes above the
tropopause, the following formula should be used:
g0
(
p > = p trop exp−
Hp,> − Hp,trop )
R TISA,trop
(3.1-20)
where altitudes Hp,> and Hp,trop are expressed in metres.
c)
Determination of Air Density
The air density, ρ, in kg/m3, is calculated from the pressure p and the temperature T at
altitude using the perfect gas law:
ρ=
10
p
RT
(3.1-21)
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Determination of Speed of Sound
The speed of sound, a, is the speed at which the pressure waves travel through a fluid and
it is given by the expression:
a= κRT
e)
(3.1-22)
CAS/TAS Conversion
The true airspeed, VTAS, is calculated as a function of the calibrated air speed, VCAS, as
follows:
1
VTAS
=
2 p p
0
1 +
µ
ρ
p
µ
2
1 + µ ρ 0 V 2 − 1 − 1
CAS
2 p0
1
µ
(3.1-23)
Similarly, VCAS is calculated as a function of VTAS as follows:
1
VCAS
2 p
p
0
=
1 +
µ ρ 0 p 0
1 + µ ρ V 2 µ − 1
TAS
2 p
1
µ
2
− 1
(3.1-24)
where symbols not previously defined are explained below:
µ=
κ -1
κ
(µ=
1
if κ = 1.4)
3.5
(3.1-25)
Note that for these conversion formulas above, the speeds VTAS and VCAS must be specified
in m/s.
f)
Mach/TAS conversion
The true airspeed, VTAS [m/s], is calculated as a function of the Mach number, M, as follows:
VTAS = M × κ R T
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g)
Mach/CAS transition altitude
The transition altitude (also called crossover altitude), Hp,trans [ft], between a given CAS,
VCAS [m/s], and a Mach number, M, is defined to be the geopotential pressure altitude at
which VCAS and M represent the same TAS value, and can be calculated as follows:
1000
Hp, trans =
⋅ [T0 ⋅ (1 − θ trans )]
0.3048
⋅
6.5
(3.1-27)
where θtrans is the temperature ratio at the transition altitude,
θ trans = (δ trans )
-
βT, <R
g0
(3.1-28)
where δtrans is the pressure ratio at the transition altitude,
κ
δ trans
12
2 κ −1
κ − 1 V
CAS
1 +
−1
2 a 0
=
κ
κ − 1 2 κ −1
−1
1 + 2 M
(3.1-29)
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3.2. TOTAL-ENERGY MODEL
The Total-Energy Model equates the rate of work done by forces acting on the aircraft to the rate of
increase in potential and kinetic energy, that is:
(Thr - D) ⋅ VTAS = mg0
dVTAS
dh
+ mVTAS
dt
dt
(3.2-1)
The symbols are defined below with metric units specified:
Thr
-
thrust acting parallel to the aircraft velocity vector [Newtons]
D
-
aerodynamic drag
[Newtons]
m
-
aircraft mass
[kilograms]
h
-
geodetic altitude
[m]
g0
-
gravitational acceleration
[9.80665 m/s2]
VTAS
d
dt
-
true airspeed
[m/s]
-
time derivative
[s-1]
Note that true airspeed is often calculated in knots and altitude calculated in feet thus requiring the
appropriate conversion factors.
Without considering the use of devices such as spoilers, leading-edge slats or trailing-edge flaps,
there are two independent control inputs available for affecting the aircraft trajectory in the vertical
plane. These are the throttle and the elevator.
These inputs allow any two of the three variables of thrust, speed, or rate of climb or descent
(ROCD) to be controlled. The other variable is then determined by equation 3.2-1. The three
resulting control possibilities are elaborated on below.
(a)
Speed and Throttle Controlled
- Calculation of Rate of Climb or Descent
Assuming that velocity and thrust are independently controlled, then equation 3.2-1 is used
to calculate the resulting rate of climb or descent (ROCD). This is a fairly common case for
climbs and descents in which the throttle is set to some fixed position (maximum climb
thrust or idle for descent) and the speed is maintained at some constant value of calibrated
airspeed (CAS) or Mach number.
(b)
ROCD and Throttle Controlled
- Calculation of Speed
Assuming that the ROCD and thrust are independently controlled, then equation 3.2-1 is
used to calculate the resulting speed.
(c)
Speed and ROCD Controlled
- Calculation of Thrust
Assuming that both ROCD and speed are controlled, then equation 3.2-1 can be used to
calculate the necessary thrust. This thrust must be within the available limits for the desired
ROCD and speed to be maintained.
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Case (a), above, is the most common such that equation 3.2-1 is most often used to calculate the
rate of climb or descent. To facilitate this calculation, equation 3.2-1 can be rearranged as follows:
(Thr - D) ⋅ VTAS = mg 0
dh
dV
dh
+ m VTAS TAS
dt
dh dt
(3.2-2)
Isolating the vertical speed on the left hand side gives:
(Thr − D) ⋅ VTAS VTAS
dh
=
1 +
dt
mg0
g0
dVTAS
dh
−1
(3.2-3)
Vertical speed is defined as the variation with time of the aircraft geodetic altitude h. The
assumption of a standard constant gravity field derives in identical geodetic and geopotential
altitudes H [RD14].
The ROCD is defined as the variation with time of the aircraft geopotential pressure altitude Hp. It is
the preferred way of presenting the performances of an aircraft as it eliminates possible variations
caused by the atmospheric conditions:
T − ∆T (Thr − D) ⋅ VTAS
ROCD =
=
dt
T
mg 0
dHp
VTAS
1 +
g 0
dVTAS
dh
−1
(3.2-4)
where :
T
-
atmosphere temperature [K];
∆T
-
temperature differential [K].
It has been shown by Renteux [RD3] that the last term can be replaced by an energy share factor
as a function of Mach number, f{M}:
V
f {M} = 1 + TAS
g 0
dVTAS
⋅
dh
−1
(3.2-5)
This leads to:
dh (Thr − D) ⋅ VTAS
=
f {M}
dt
mg 0
ROCD =
dHP
T − ∆T (Thr − D) ⋅ VTAS
=
f {M}
dt
T
mg 0
(3.2-6)
(3.2-7)
This energy share factor f{M} specifies how much of the available power is allocated to climb as
opposed to acceleration while following a selected speed profile during climb.
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For several common flight conditions, equation 3.2-5 can be rewritten as is done below. A more
comprehensive description of this process can be found in [RD7]:
(a)
Constant Mach number in stratosphere (i.e. above tropopause)
f{M} = 1.0
(3.2-8)
Note that above the tropopause the air temperature and the speed of sound are constant.
Maintaining a constant Mach number therefore requires no acceleration and all available
power can be allocated to a change in altitude.
(b)
Constant Mach number below tropopause:
κ R β T,< 2 T − ∆T
f {M} = 1 +
M
2 g0
T
−1
(3.2-9)
In this case, for a typical Mach number of 0.8 the energy share factor allocated to climb is
1.09.
This number is greater than 1 because below the tropopause, the temperature and thus,
speed of sound decreases with altitude. Maintaining a constant Mach number during climb
thus means that the true airspeed decreases with altitude. Consequently, the rate of climb
benefits from not only all the available power but also a transfer of kinetic energy to
potential energy.
(c)
Constant Calibrated Airspeed (CAS) below tropopause
κ
−1
κ R β T,< 2 T − ∆T κ - 1 2 κ −1 κ - 1 2 κ −1
f {M} = 1 +
M
+ 1 +
M 1 +
M
− 1
2 g0
T
2
2
−1
(3.2-10)
In this case the energy share factor is less than one. A Mach number of 0.6 for example
yields an energy share factor of 0.85.
This number is less than 1 because as density decreases with altitude, maintaining a
constant CAS during climb requires maintaining a continual increase in true airspeed. Thus,
some of the available power needs to be allocated to acceleration leaving the remainder for
climb.
(d)
Constant Calibrated Airspeed (CAS) above tropopause.
−1
κ
κ - 1 2 κ −1 κ - 1 2 κ −1
f {M} = 1 + 1 +
M 1 +
M
− 1
2
2
−1
(3.2-11)
This formula is identical to (3.2-10), except that βT is now null since we are above the
tropopause.
The energy share factors given above apply equally well to descent as to climb. The
difference being that the available power is negative for descent.
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In cases where neither constant Mach number nor constant CAS is maintained, the
following energy share factors are used:
•
•
•
•
acceleration in climb:
deceleration in descent:
deceleration in climb:
acceleration in descent:
f{M} = 0.3
f{M} = 0.3
f{M} = 1.7
f{M} = 1.7
Note that, for the cases of acceleration in climb or deceleration in descent, the majority of
the available power is devoted to a change in speed.
For the cases of deceleration in climb or acceleration in descent, the energy share factor is
greater than 1 since the change of altitude benefits from a transfer of kinetic energy.
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3.3. AIRCRAFT TYPE
Three values are specified for aircraft type, these being the number of engines, neng, the engine
type and the wake category.
The engine type can be one of three values:
•
•
•
Jet
Turboprop
Piston
The wake category can also be one of four values:
•
•
•
•
J : jumbo
H : heavy
M: medium
L : light
Note that ICAO associates a wake category with each aircraft type designator [RD2].
3.4. MASS
Four mass values are specified for each aircraft in tonnes:
mmin
mmax
mref
mpyld
- minimum mass
- maximum mass
- reference mass
- maximum payload mass
Note that the specified mass limits are taken from aircraft performance reference data which is
available in the BADA library. In function of specific aircraft certified limitations, a particular aircraft
version of a given aircraft type (model) may have different limits. More details on the way the mass
limits are selected in BADA is provided in [RD6].
Aircraft operating speeds vary with the aircraft mass. This variation is calculated according to the
formula below:
V = Vref ×
m
m ref
(3.4-1)
In this formula, the aircraft reference speed Vref is given for the reference mass mref. The speed at
another mass, m, is then calculated as V.
An example of an aircraft speed which can be calculated via this formula is the stall speed, Vstall.
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3.5. FLIGHT ENVELOPE
(a)
Maximum Speed and Altitude
The maximum speed and altitude for an aircraft are expressed in terms of the following six
parameters:
VMO
-
maximum operating speed (CAS) [kt]
MMO
-
maximum operational Mach number
hMO
-
maximum operating altitude [ft] above standard MSL
hmax
-
maximum altitude [ft] above standard MSL at MTOW under ISA
conditions (allowing about 300 ft/min of residual rate of climb)
Gw
-
mass gradient on hmax [ft/kg]
Gt
-
temperature gradient on hmax [ft/K]
The maximum altitude for any given mass is:
h max/act = MIN [ hMO , h max + G t × (∆T − C Tc,4 ) + G w × (m max − m act )]
(3.5-1)
where: ∆T is the temperature deviation from ISA [K]
mact is the actual aircraft mass [kg]
with:
Gw ≥ 0
Gt ≤ 0
if (∆T - CTc,4) < 0, then : (∆T - CTc,4) = 0
Formula 3.5-1 should not be executed when the hmax value in the OPF file is set to 0 (zero). In that
case the maximum altitude is always hMO.
Note that the given speed and altitude limits are taken from available reference data: depending
upon specific certifications, a particular aircraft of a given type may present different limits.
(b)
Minimum Speed
The minimum speed for the aircraft is in function of aircraft stall speed and specified as follows:
Vmin = C Vmin,TO × Vstall
if in take-off
(3.5-2)
Vmin = C Vmin × Vstall
otherwise
(3.5-3)
Note: See Section 3.6.2 for minimum speed at high altitude for jet aircraft and Section 5.7 for the
values of the minimum speed coefficients.
Here the speeds are specified in terms of CAS. The stall speed depends upon the configuration.
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Specifically, five different configurations are specified with a stall speed, (Vstall)i, and configuration
threshold altitude, Hmax,i, given for each:
TO - take-off configuration
(Vstall)TO
(in climb up to Hmax,TO AGL)
IC - initial climb configuration
(Vstall)IC
(in climb between Hmax,TO and Hmax,IC AGL)
CR - cruise (clean) configuration
(Vstall)CR
(in climb above Hmax,IC AGL,
in descent above Hmax,AP AGL,
in descent below Hmax,AP AGL when
V ≥ Vmin,cruise + 10 kt)
AP - approach configuration
(Vstall)AP
(in descent between Hmax,AP AGL and Hmax,LD AGL when
V < Vmin,cruise + 10 kt,
in descent below Hmax,LD AGL when
Vmin,cruise + 10 kt > V ≥ Vmin,approach + 10 kt)
LD - landing configuration
(Vstall)LD
(in descent below Hmax,LD AGL when
V < Vmin,approach + 10 kt)
The threshold altitudes are expressed in terms of geopotential pressure altitude. However, when
aircraft operations close to the ground are considered, one has to account for airport/runway
elevation6. The pressure altitude thresholds provided above correspond to geopotential pressure
altitude Above Ground Level (AGL).
The stall speeds correspond to a minimum stall speed and not a 1-g stall speed.
Also, the BADA model assumes that for any aircraft these stall speeds have the following
relationship:
(Vstall ) CR ≥ (Vstall )IC ≥ (Vstall ) TO ≥ (Vstall ) AP ≥ (Vstall )LD
The configuration specific values are listed in Section 5.6. The speeds V used during the descent,
approach and landing phases are defined in Section 4.3.
6 Measured from Mean Sea Level (MSL).
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3.6.
AERODYNAMICS
3.6.1. Aerodynamic Drag
The lift coefficient, CL, is determined assuming that the flight path angle is zero. However, a
correction for a bank angle is made.
CL =
2 ⋅ m ⋅ g0
(3.6-1)
ρ ⋅ VTAS ⋅ S ⋅ cos φ
2
Under nominal conditions, the drag coefficient, CD is specified as a function of the lift coefficient CL
as follows:
C D = C D0,CR + C D2,CR × (C L )
2
(3.6-2)
Formula 3.6-2 is valid for all situations except for the approach and landing where other drag
coefficients are to be used.
In the approach configuration (as defined in Section 3.5) a different flap setting is used, and
formula 3.6-3 should be applied:
C D = C D0,AP + C D2,AP × (C L )
2
(3.6-3)
In the landing configuration (as defined in Section 3.5) a different flap setting is used, and formula
3.6-4 should be applied:
C D = C D0,LDG + C D0,∆LDG + C D2,LDG × (C L )
2
(3.6-4)
The value of CD0,∆LDG represents drag increase due to the landing gear. The values of CD0,LD in the
OPF files were all determined for the landing flap setting mentioned in the OPF file.
The drag force [Newtons] is then determined from the drag coefficient in the standard manner:
C D ⋅ ρ ⋅ VTAS ⋅ S
2
2
D=
(3.6-5)
Where :
ρ is the air density [kg/m3]
S is the wing reference area [m2]
VTAS is the true airspeed [m/s].
Note that the air density is a function of altitude as described in Section 3.1.
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The above equations thus result in eight coefficients for the specification of drag:
S
CD0,CR
CD2,CR
CD0,AP
CD2,AP
CD0,LD
CD2,LD
CD0,∆LDG
In case the CD0,AP, CD2,AP, CD0,LD, CD2,LD and CD0,∆LDG coefficients (referred to as “non-clean” data in
this document) are set to 0 (zero) in the OPF file, expression 3.6-2 will be used in all cases.
3.6.2. Low Speed Buffeting Limit (jet aircraft only)
For jet aircraft a low speed buffeting limit has been introduced. This buffeting limit is expressed as
a Mach number and can be determined using the following equation:
k × M 3 - C Lbo (M=0) × M 2 +
W
= 0
S ⋅ p ⋅ 0.583
(3.6-6)
where:
k is lift coefficient gradient
CLbo (M=0) is initial buffet onset lift coefficient for M=0
p is actual pressure [Pa]
M is Mach number
S is the wing reference area [m2]
W is aircraft weight [N]
Note that the factor of 0.583 gives a 0.2 g margin.
The k and CLbo (M=0) parameters have been determined for nearly all jet aircraft in BADA 3.9. If the k
and CLbo (M=0) parameters in the OPF file are set to 0 (zero), the minimum speed is given by
expressions 3.5-2 and 3.5-3. Otherwise, the solution for M in Formula 3.6-6 can be obtained using
the method given in Appendix B. The buffeting limit should be applied as a minimum speed in the
following way:
- If (Hp ≥ 15,000 ft)
then: Vmin= MAX(Vmin,stall, Mb)
- If (Hp < 15,000 ft)
then: Vmin= Vmin,stall
where: Hp
is the geopotential pressure altitude
Mb
is the lowest positive solution of expression 3.6-6
Vmin,stall
is given by expressions 3.5-2 and 3.5-3
Note that the units of the two values Vmin,stall and Mb inside the MAX() expression should be the
same.
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3.7. ENGINE THRUST
The BADA model provides coefficients that allow the calculation of the following thrust levels:
• maximum climb and take-off,
• maximum cruise,
• descent.
The thrust is calculated in Newtons and includes the contribution from all engines. The subsections
below provide the equations for each of the thrust conditions.
3.7.1. Maximum Climb and Take-Off Thrust
The maximum climb thrust at standard atmosphere conditions, (Thrmax
Newtons as a function of the following information:
•
•
•
•
climb)ISA,
is calculated in
engine type: either Jet, Turboprop or Piston;
geopotential pressure altitude, Hp [ft];
true airspeed, VTAS [kt];
temperature deviation from standard atmosphere, ∆T [K].
The equations corresponding to the three engine types are given below.
Hp
2
= C Tc,1 × 1 + C Tc,3 × Hp
C
Tc,2
Jet:
(Thrmax climb )ISA
Turboprop:
(Thrmax climb )ISA =
Piston:
(Thrmax climb )ISA = C Tc,1 × 1 -
C Tc,1
VTAS
(3.7-1)
Hp
+ C Tc,3
C Tc,2
(3.7-2)
Hp C Tc,3
+
C Tc,2 VTAS
(3.7-3)
× 1 -
For all engine types, the maximum climb thrust is corrected for temperature deviations from
standard atmosphere, ∆T, in the following manner:
Thr max climb = (Thrmax climb )ISA × ( 1 - C Tc,5 ⋅ ∆Teff )
(3.7-4)
Where:
∆Teff = ∆T – CTc,4
(3.7-5)
0.0 ≤ ∆Teff x CTc,5 ≤ 0.4
(3.7-6)
CTc,5 ≥ 0.0
(3.7-7)
with the limits:
and:
This maximum climb thrust is used for both take-off and climb phases.
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3.7.2. Maximum Cruise Thrust
The normal cruise thrust is by definition set equal to drag (Thr = D). However, the maximum
amount of thrust available in cruise situation is limited. The maximum cruise thrust is calculated as
a ratio of the maximum climb thrust given by expression 3.7-4, that is:
(Thrcruise )MAX = C Tcr × Thr max climb
(3.7-8)
The coefficient CTcr is currently uniformly set for all aircraft (see Section 5.5).
3.7.3. Descent Thrust
Descent thrust is calculated as a ratio of the maximum climb thrust given by expression 3.7-4, with
different correction factors used for high and low altitudes, and approach and landing
configurations (see Section 3.5), that is:
if Hp > Hp,des:
Thrdes,high = C Tdes,high × Thrmax climb
(3.7-9)
Cruise configuration:
Thrdes,low = C Tdes,low × Thrmax climb
(3.7-10)
Approach configuration:
Thrdes,app = C Tdes,app × Thrmax climb
(3.7-11)
Landing configuration:
Thrdes,ld = C Tdes,ld × Thrmax climb
(3.7-12)
if Hp ≤ Hp,des:
Note that for those models where “non-clean” data (see Section 3.6.1) is available, Hp,des cannot be
below Hmax,AP.
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3.8. REDUCED CLIMB POWER
The reduced climb power has been introduced to allow the simulation of climbs using less than the
maximum climb setting. In day-to-day operations, many aircraft use a reduced setting during climb
in order to extend engine life and save cost. The correction factors that are used to calculate the
reduction in power have been obtained in an empirical way and have been validated with the help
of air traffic controllers.
In BADA, climbs that are performed using the full climb power will result in profiles that match the
reference data that is found in the Flight Manual of the aircraft. Climbs with reduced power will give
a realistic profile.
C pow,red = 1 - C red ×
m max − m act
m max − m min
(3.8-1)
The value of Cred is a function of the aircraft type and is given in Section 5.11.
Nevertheless:
If Hp < (0.8·hmax):
Cred = f (aircraft type)
(see Section 5.11)
Cred = 0
[dimensionless]
Else
where hmax is given by expression 3.5-1.
The power reduction Cpow,red is to be applied during the climb phase in expression 3.2-7, which
becomes:
ROCD =
24
dHp
dt
=
T - ∆T (Thrmax climb − D) ⋅ VTAS ⋅ C pow,red
⋅ f {M}
T
m ⋅ g0
(in climb)
(3.8-2)
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3.9. FUEL CONSUMPTION
3.9.1. Jet and Turboprop Engines
For the jet and turboprop engines, the thrust specific fuel consumption, η [kg/(min·kN)], is specified
as a function of the true airspeed, VTAS [kt]:
jet:
V
η = C f1 × 1 + TAS
C f2
(3.9-1)
turboprop:
V
η = C f1 × 1 - TAS
C f2
(3.9-2)
VTAS
×
1000
The nominal fuel flow, fnom [kg/min], can then be calculated using the thrust, Thr:
jet/turboprop:
fnom = η × Thr
(3.9-3)
These expressions are used in all flight phases except during idle descent and cruise, where the
following expressions are to be used.
The minimum fuel flow, fmin [kg/min], corresponding to idle thrust descent conditions for both jet and
turboprop engines, is specified as a function of the geopotential pressure altitude, Hp [ft], that is:
jet/turboprop:
H
fmin = C f3 1 - P
C f4
(3.9-4)
Note that for both jet and turboprop engines, the idle thrust part of the descent stops when the
aircraft switches to approach and landing configuration (see Section 3.5), at which point thrust is
generally increased. Hence, the calculation of fuel flow during approach and landing phases shall
be based on the nominal fuel flow (expressions 3.7-11, 3.7-12 and 3.9-3), and limited to the
minimum fuel flow (expression 3.9-4) if necessary:
jet/turboprop:
fap/ld = MAX (fnom, fmin)
(3.9-5)
The cruise fuel flow, fcr [kg/min], is calculated using the thrust specific fuel consumption η, the
thrust Thr, and a cruise fuel flow factor, Cfcr:
jet/turboprop:
f cr = η × Thr × C fcr
(3.9-6)
For the moment the cruise fuel flow correction factor has been established for a number of aircraft
types whenever the reference data for cruise fuel consumption is available. This factor has been
set to 1 (one) for all the other aircraft models.
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3.9.2. Piston Engines
For piston engines, the nominal fuel flow, fnom [kg/min], is specified to be a constant, that is:
fnom = C f1
(3.9-7)
This expression is used in all flight phases except during descent and cruise, where the following
expressions are to be used.
The minimum fuel flow, fmin [kg/min], corresponding to descent conditions for piston engines, is
specified to be a constant:
fmin = C f3
(3.9-8)
The cruise fuel flow, fcr [kg/min], is calculated using a cruise fuel flow factor, Cfcr:
f cr = C f1 × C fcr
(3.9-9)
For the moment the cruise fuel flow correction factor has been established for a number of aircraft
types whenever the reference data for cruise fuel consumption is available. This factor has been
set to 1 (one) for all the other aircraft models.
3.10. GROUND MOVEMENT
Four values are specified that can be of use when simulating ground movements. These
parameters are:
• TOL:
FAR Take-Off Length [m] with MTOW on a dry, hard, level runway under ISA
conditions and no wind.
• LDL:
FAR Landing Length [m] with MLW on a dry, hard, level runway under ISA
conditions and no wind.
• span:
aircraft wingspan [m]
• length:
aircraft length [m]
Note that currently the value of the MLW is not provided in BADA. Apart from these model specific
parameters, there are also a number of ground speeds defined as general parameters in Section
5.10.
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3.11. SUMMARY OF OPERATIONS PERFORMANCE PARAMETERS
A summary of the parameters specified by the BADA operations performance model is supplied in
Table 3-1 below. This table excludes those parameters that have been set to zero.
Detailed information on how these parameters have been obtained during the process of BADA
aircraft model identification using the aircraft performance reference documents is provided in
[RD6].
Important notice: Parameters listed in bold in the Table 3-1 below should not be modified by the
user as such modifications may impact the validity of the data provided in [RD13].
Table 3-1: BADA Operations Performance Parameter Summary
Model Category
Aircraft type
Symbols
Units
Description
neng
dimensionless
number of engines
engine type
string
either Jet, Turboprop or Piston
wake category
string
either J, H, M or L
Mass
mref
tonnes
reference mass
(4 values)
mmin
tonnes
minimum mass
mmax
tonnes
maximum mass
mpyld
tonnes
maximum payload mass
Flight envelope
VMO
knots (CAS)
maximum operating speed
(6 values)
MMO
dimensionless
maximum operating Mach number
hMO
feet
maximum operating altitude
hmax
feet
max. altitude at MTOW and ISA
Gw
feet/kg
weight gradient on max. altitude
Gt
feet/K
temperature gradient on max. altitude
S
m2
reference wing surface area
CD0,CR
dimensionless
parasitic drag coefficient (cruise)
CD2,CR
dimensionless
induced drag coefficient (cruise)
CD0,AP
dimensionless
parasitic drag coefficient (approach)
CD2,AP
dimensionless
induced drag coefficient (approach)
CD0,LD
dimensionless
parasitic drag coefficient (landing)
CD2,LD
dimensionless
induced drag coefficient (landing)
CD0,∆∆LDG
dimensionless
parasite drag coef. (landing gear)
(Vstall)i
knots (CAS)
stall speed [TO, IC, CR, AP, LD]
CLbo (M=0)
dimensionless
Buffet onset lift coef. (jet only)
(3 values)
Aerodynamics
(16 values for jet
aircraft, only 14
values for others)
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Model Category
Engine thrust
(12 values)
Symbols
Units
Description
K
dimensionless
Buffeting gradient (jet only)
CTc,1
Newton (jet/piston)
knot-Newton (turboprop)
1st max. climb thrust coefficient
CTc,2
feet
2nd max climb thrust coefficient
2
CTc,3
1/feet (jet)
Newton (turboprop)
knot-Newton (piston)
3rd max. climb thrust coefficient
CTc,4
K
1st thrust temperature coefficient
CTc,5
1/K
2nd thrust temperature coefficient
CTdes,low
dimensionless
low altitude descent thrust coefficient
CTdes,high
dimensionless
high altitude descent thrust
coefficient
Hp,des
feet
transition altitude for calculation of
descent thrust
CTdes,app
dimensionless
approach thrust coefficient
CTdes,ld
dimensionless
landing thrust coefficient
Vdes,ref
knots
reference descent speed (CAS)
Mdes,ref
dimensionless
reference descent Mach number
Cf1
kg/(min·kN) (jet)
kg/(min·kN·knot)
(turboprop)
kg/min (piston)
1st thrust specific fuel consumption
coefficient
Cf2
knots
2nd thrust specific fuel consumption
coefficient
Cf3
kg/min
1st descent fuel flow coefficient
Cf4
feet
2nd descent fuel flow coefficient
Cfcr
dimensionless
cruise fuel flow correction coefficient
Ground
movement
TOL
m
take-off length
LDL
m
landing length
(4 values)
span
m
wingspan
length
m
length
Fuel flow
(5 values)
Note that the following coefficients can have negative values:
K, Gt, CTc,2, CTc,3, CTdes,low, CTdes,high, Cf2, Cf4.
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4. AIRLINE PROCEDURE MODELS
This section defines the standard airline procedures, which are parameterised by the BADA airline
procedure models. Definition of the standard airline procedures in BADA is driven by a requirement
to provide means of simulating standard or nominal aircraft operations using different simulation
and modelling tools for various ATM applications.
The BADA airline procedure model is provided for three separate flight phases: climb, cruise and
descent. For each of these phases and each aircraft model, the BADA airline procedure model
requires the following information to determine aircraft speed schedule:
1. BADA airline procedure default speeds provided in Airline Procedure File (APF):
V1 - standard CAS [knots] below 10,000 ft;
V2 - standard CAS [knots] between 10,000 ft and Mach transition altitude;
M - standard Mach number above Mach transition altitude;
where the Mach transition altitude is defined in Section 3.1 (g).
2. Stall speeds for take-off and landing configurations provided in Operations Performance
File (OPF)
3. Coefficients provided in the Section 5.7 and 5.8
The process of definition of the BADA airline procedure default speeds and choice of aircraft
configurations in function of flight phase is described in [RD6]. The airline procedure model below
10,000 ft with corresponding coefficients (mentioned under item 3 above) have been defined taking
into account aircraft manufacturer’s performance reference data and aircraft operational data
available at EUROCONTROL.
The fact that the way aircraft is operated varies significantly in function of specific airspace
procedures and operating policies of locally dominant airlines is widely recognised. It is for that
reason that the resulting speed schedules of the BADA standard airline procedure model may
differ from a geographical location or of an aerospace’s specific aircraft operation.
To account for the local aircraft operation characteristics and improve conformance of the
simulated aircraft behaviour with real operations, the user of BADA is given a possibility to modify
the BADA default speeds (as provided in APF file). The change of speed related APF parameters
should be done in accordance with the BADA modelling procedure described in the Chapter 2.2.3
of [RD6].
However, the stall speeds (as provided in OPF file) and coefficients detailed in Section 5.7 and 5.8
are not subject to modification. The BADA User should not modify them.
The altitude levels, used for determination of CAS speed schedules and provided in the following
chapters, are expressed in terms of geopotential pressure altitude. However, different reference
datums for altitude measurement7 may be applied in function of the user application and its
functional design choices.
The BADA Airline Procedure Model only identifies the possibility to introduce notion of different
altitude altimetry for calculation of the CAS speed schedules in the user application. The
implementation decision is left to the application owner.
7 Such as use of standard operational pressure settings used in aviation: QNH for MSL pressure, QFE for pressure at the airport
reference point or QNE corresponding to standard MSL1013 hPa.These can be selected through the altimeter’s pressure setting knob in
the aircraft.
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4.1. CLIMB
The following parameters are defined for each aircraft type to characterise the climb phase:
Vcl,1
-
standard climb CAS [knots] between 1,500/6,000 and 10,000 ft
Vcl,2
-
standard climb CAS [knots] between 10,000 ft and Mach transition altitude
Mcl
-
standard climb Mach number above Mach transition altitude
Note that the climb speed schedule shall determine an increasing speed from take-off to Vcl,1. To
ensure that monotony, it is recommended to determine the speed schedule from the highest
altitude to the lowest one, and to use at each step the speed of the higher altitude range as a
ceiling value for the lower altitude range.
For jet aircraft the following CAS schedule is assumed, based on the parameters mentioned
above and the take-off stall speed:
from 0 to 1,499 ft
CVmin · (Vstall)TO + VdCL,1
(4.1-1)
from 1,500 to 2,999 ft
CVmin · (Vstall)TO + VdCL,2
(4.1-2)
from 3,000 to 3,999 ft
CVmin · (Vstall)TO + VdCL,3
(4.1-3)
from 4,000 to 4,999 ft
CVmin · (Vstall)TO + VdCL,4
(4.1-4)
from 5,000 to 5,999 ft
CVmin · (Vstall)TO + VdCL,5
(4.1-5)
from 6,000 to 9,999 ft
min (Vcl,1, 250 kt)
from 10,000 ft to Mach transition altitude
Vcl,2
above Mach transition altitude
Mcl
For turboprop and piston aircraft the following CAS schedule is assumed:
from 0 to 499 ft
CVmin · (Vstall)TO + VdCL,6
(4.1-6)
from 500 to 999 ft
CVmin · (Vstall)TO + VdCL,7
(4.1-7)
from 1,000 to 1,499 ft
CVmin · (Vstall)TO + VdCL,8
(4.1-8)
from 1,500 to 9,999 ft
min (Vcl,1, 250 kt)
from 10,000 ft to Mach transition altitude
Vcl,2
above Mach transition altitude
Mcl
The take-off stall speed, (Vstall)TO, must be corrected for the difference in aircraft mass from the
reference mass using formula 3.4-1. The values for VdCL,i can be found in Section 5.
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4.2. CRUISE
The following parameters are defined for each aircraft type to characterise the cruise phase:
Vcr,1
-
standard cruise CAS [knots] between 3,000 and 10,000 ft
Vcr,2
-
standard cruise CAS [knots] between 10,000 ft and Mach transition altitude
Mcr
-
standard cruise Mach number above Mach transition altitude
For jet aircraft the following CAS schedule is assumed:
from 0 to 2,999 ft
min (Vcr,1, 170 kt)
from 3,000 to 5,999 ft
min (Vcr,1, 220 kt)
from 6,000 to 13,999 ft
min (Vcr,1, 250 kt)
from 14,000 ft to Mach transition altitude
Vcr,2
above Mach transition altitude
Mcr
For turboprop and piston aircraft the following CAS schedule is assumed:
from 0 to 2,999 ft
min (Vcr,1, 150 kt)
from 3,000 to 5,999 ft
min (Vcr,1, 180 kt)
from 6,000 to 9,999 ft
min (Vcr,1, 250 kt)
from 10,000 ft to Mach transition altitude
Vcr,2
above Mach transition altitude
Mcr
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4.3. DESCENT
The following parameters are defined for each aircraft type to characterise the descent phase:
Vdes,1
-
standard descent CAS [knots] between 3,000/6,000 and 10,000 ft
Vdes,2
-
standard descent CAS [knots] between 10,000 ft and Mach transition altitude
Mdes
-
standard descent Mach number above Mach transition altitude
Note that the descent speed schedule shall determine a decreasing speed from Vdes,1 to landing.
To ensure that monotony, it is recommended to evaluate the speed schedule from the highest
altitude to the lowest one, and to use at each step the speed of the higher altitude range as a
ceiling value for the lower altitude range.
For jet and turboprop aircraft the following CAS schedule is assumed, based on the above
parameters and the landing stall speed:
from 0 to 999 ft
CVmin · (Vstall)LD + VdDES,1
(4.3-1)
from 1,000 to 1,499 ft
CVmin · (Vstall)LD + VdDES,2
(4.3-2)
from 1,500 to 1,999 ft
CVmin · (Vstall)LD + VdDES,3
(4.3-3)
from 2,000 to 2,999 ft
CVmin · (Vstall)LD + VdDES,4
(4.3-4)
from 3,000 to 5,999 ft
min (Vdes,1, 220)
from 6,000 to 9,999 ft
min (Vdes,1, 250)
from 10,000 ft to Mach transition altitude
Vdes,2
above Mach transition altitude
Mdes
For piston aircraft the following CAS schedule is assumed:
from 0 to 499 ft
CVmin · (Vstall)LD + VdDES,5
(4.3-5)
from 500 to 999 ft
CVmin · (Vstall)LD + VdDES,6
(4.3-6)
from 1000 to 1,499 ft
CVmin · (Vstall)LD + VdDES,7
(4.3-7)
from 1,500 to 9,999 ft
Vdes,1
from 10,000 ft to Mach transition altitude
Vdes,2
above Mach transition altitude
Mdes
The landing stall speed, (Vstall)LD, must be corrected for the difference in aircraft mass from the
reference mass using formula 3.4-1. The values for VdDES,i can be found in Section 5.
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5. GLOBAL AIRCRAFT PARAMETERS
5.1. INTRODUCTION
A number of parameters that have been described in Section 3 (Operations Performance Model)
and Section 4 (Airline Procedure Model) have values that are independent of the aircraft type or
model for which they are used. The values of these and other parameters which have general use,
have been put in the Global Parameters File (BADA.GPF). This increases the flexibility and allows
an easier evaluation of the values that are used.
The next section gives an overview of the parameters that are defined in the Global Parameters
File. If relevant, it also indicates the formula in which the parameter should be used.
5.2. MAXIMUM ACCELERATION
Maximum acceleration parameters are used to limit the increment in TAS (longitudinal) or ROCD
(normal). Two parameters are defined:
Value [ft/s2]:
Name:
Description:
al,max (civ)
maximum longitudinal acceleration for civil flights
2.0
an,max (civ)
maximum normal acceleration for civil flights
5.0
The two acceleration limits are to be used in the following way:
longitudinal acceleration:
Vk - Vk -1
≤
normal acceleration:
γ k - γ k -1
≤
where,
a l,max (civ) ∆t
a n,max (civ) ∆t
V
.
h
γ = sin
V
(5.2-1)
(5.2-2)
-1
(5.2-3)
and,
γ
is the climb/descent angle,
V
is the true airspeed [ft/s],
k, k-1
indicate values at update intervals k and k-1,
∆t
is the time interval between k and k-1 [s]
The values for the maximum longitudinal acceleration for military flights, al,max (mil), and for the
maximum normal acceleration for military flights, an,max (mil), are currently undefined.
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5.3. BANK ANGLES
Nominal and maximum bank angles are defined separately for military and civil flights. These bank
angles can be used to calculate nominal and maximum rate of turns.
Name:
Description:
Value [deg]:
φnom,civ (TO,LD)
Nominal bank angles for civil flight during TO and LD
15
φnom,civ (OTHERS)
Nominal bank angles for civil flight during all other phases
35
φnom,mil
Nominal bank angles for military flight (all phases)
50
φmax,civ (TO,LD)
Maximum bank angles for civil flight during TO and LD
25
φmax,civ (HOLD)
Maximum bank angles for civil flight during HOLD
35
φmax,civ (OTHERS)
Maximum bank angles for civil flight during all other phases
45
φmax,mil
Maximum bank angles for military flight (all phases)
70
The rate of turn, ϕ& , is calculated as a function of the bank angle:
ϕ& =
g0
× tan (φ )
VTAS
(5.3-1)
5.4. EXPEDITED DESCENT
The expedited descent factor is to be used as a drag multiplication factor during expedited
descents in order to simulate use of spoilers:
Name:
Description:
Value [ - ]:
Cdes,exp
Expedited descent factor
1.6
The drag during an expedited descent is calculated using the nominal drag (see Section 3.6.1):
Ddes,exp = Cdes,exp · Dnom
(5.4-1)
5.5. THRUST FACTORS
Maximum take-off and maximum cruise thrust factors have been specified. The CTh,TO factor is no
longer used since BADA 3.0. The CTcr factor is to be used in expression 3.7-8.
34
Name:
Description:
Value [ - ]:
CTh,TO
Take-off thrust coefficient
1.2
CTcr
Maximum cruise thrust coefficient
0.95
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5.6. CONFIGURATION ALTITUDE THRESHOLD
For 4 configurations, altitude thresholds have been specified in BADA: take-off (TO), initial climb
(IC), approach (AP) and landing (LD). Note that the selection of the take-off and initial climb
configurations is defined only with the altitude. The selection of the approach and landing
configurations is done through the use of air speed and altitude (see Section 3.5), while the
altitudes at which the configuration change takes place should not be higher than the ones given
below. The altitude values are expressed in terms of geopotential pressure altitude.
Name:
Description:
Value [ft]:
Hmax,TO
Maximum altitude threshold for take-off
400
Hmax,IC
Maximum altitude threshold for initial climb
2,000
Hmax,AP
Maximum altitude threshold for approach
8,000
Hmax,LD
Maximum altitude threshold for landing
3,000
5.7. MINIMUM SPEED COEFFICIENTS
Two minimum speed coefficients are specified, which are to be used in expressions 3.5-2 and 3.53 and (for CVmin only) in Section 4.1 and 4.3:
Name:
Description:
Value [ - ]:
CVmin,TO
Minimum speed coefficient for take-off
1.2
CVmin
Minimum speed coefficient (all other phases)
1.3
5.8. SPEED SCHEDULES
The speed schedules applicable below FL100 for climb and descent are based on a factored stall
speed plus increment valid for a specified geopotential pressure altitude range.
Name:
Description:
VdCL,1
Climb speed increment below 1500 ft (jet)
5
VdCL,2
Climb speed increment below 3000 ft (jet)
10
VdCL,3
Climb speed increment below 4000 ft (jet)
30
VdCL,4
Climb speed increment below 5000 ft (jet)
60
VdCL,5
Climb speed increment below 6000 ft (jet)
80
VdCL,6
Climb speed increment below 500 ft (turbo/piston)
20
VdCL,7
Climb speed increment below 1000 ft (turbo/piston)
30
VdCL,8
Climb speed increment below 1500 ft (turbo/piston)
35
VdDES,1
Descent speed increment below 1000 ft (jet/turboprop)
5
VdDES,2
Descent speed increment below 1500 ft (jet/turboprop)
10
VdDES,3
Descent speed increment below 2000 ft (jet/turboprop)
20
VdDES,4
Descent speed increment below 3000 ft (jet/turboprop)
50
VdDES,5
Descent speed increment below 500 ft (piston)
5
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VdDES,6
Descent speed increment below 1000 ft (piston)
10
VdDES,7
Descent speed increment below 1500 ft (piston)
20
These values are to be used in the expressions in Section 4.1 and 4.3.
5.9. HOLDING SPEEDS
The holding speeds that are to be used to calculate holding areas are defined according to the
ICAO standards:
Name:
Description:
Value [KCAS]:
Vhold,1
Holding speed below FL140
230
Vhold,2
Holding speed between FL140 and FL200
240
Vhold,3
Holding speed between FL200 and FL340
265
Vhold,4
Holding speed above FL340 [Mach]
0.83
Note that the holding speeds that are used by individual aircraft may vary between types.
5.10. GROUND SPEEDS
A number of ground speeds are defined for the simulation of ground movement. For the moment,
no distinction between aircraft type or engine type is made. The following speeds have been
defined:
Name:
Description:
Value [KCAS]:
Vbacktrack
Runway backtrack speed
35
Vtaxi
Taxi speed
15
Vapron
Apron speed
10
Vgate
Gate speed
5
The runway backtrack speed is the speed the aircraft will maintain when it backtracks across the
runway. The taxi speed is used anywhere between the runway and the apron area. The apron
speed is used in the apron area while the gate speed is used for all manoeuvring between the gate
position and the apron.
5.11. REDUCED POWER COEFFICIENT
The reduced power coefficients are defined for the three different engine types. It is stressed that
the values given below were found in an empirical way and have been validated with the help of air
traffic controllers:
Name:
Description:
Value [ - ]:
Cred,turbo
Maximum reduction in power for turboprops
0.25
Cred,piston
Maximum reduction in power for pistons
0.0
Cred,jet
Maximum reduction in power for jets
0.15
The coefficients should be used in Formula 3.8-1.
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6. FILE STRUCTURE
6.1. FILE TYPES
All data provided by BADA Revision 3.9 is organised into six types of files:
•
•
•
•
•
•
•
three Synonym Files,
a set of Operations Performance Files,
a set of Airline Procedure Files,
a set of Performance Table Files,
a set of Performance Table Data,
a Global Parameter File.
Three Synonym Files have the names:
SYNONYM.LST
SYNONYM.NEW
SYNONYM_ALL.LST
The files provide a list of all the aircraft types which are supported by BADA and indicate whether
the aircraft type is supported directly (through provision of parameters in other files) or supported
by equivalence (through indicating an equivalent aircraft type that is supported directly). In addition
to that, SYNONYM_ALL.LST file provides the information on history and evolution of the ICAO
aircraft designators over the years. The format of the files is described in Section 6.3.
•
There is one Operations Performance File (OPF) provided for each aircraft type which is
directly supported. This file specifies parameter values for the mass, flight envelope, drag,
engine thrust and fuel consumption that are described in Section 3. Details on the format of the
OPF file are given in Section 6.4.
•
There is one Airline Procedures File (APF) for each directly supported aircraft type. This file
specifies the nominal manoeuvre speeds that are described in Section 4. Details on the format
of the APF file are given in Section 6.5.
•
There is one Performance Table File (PTF) for each directly supported aircraft type. This file
contains a summary table of speeds, climb/descent rates and fuel consumption at various flight
levels. Details on the format of the PTF file are given in Section 6.6.
•
There is one Performance Table Data (PTD) file for each directly supported aircraft type. This
file contains a detailed table of computed performance values at various flight levels. Details on
the format of the PTD file are given in Section 6.7.
•
Finally there is one Global Parameter File which is named BADA.GPF. This file contains
parameters that are described in Section 5 and are valid for all aircraft or a group of aircraft (for
instance all civil flights or all jet aircraft). Details on the format of the GPF file are given in
Section 6.8.
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The names of the OPF, APF, PTF and PTD files are based on the ICAO designation code for the
aircraft type. With only the exception of the generic military fighter aircraft types (FGTH, FGTL,
FGTN), this code is the same as the International Civil Aviation Organisation (ICAO) designator
code for the aircraft type [RD2]. That is:
Operations Performance File name:
<ICAO_code>__.OPF
Airline Procedures File name:
<ICAO_code>__.APF
Performance Table File name:
<ICAO_code>__.PTF
Performance Table Data name:
<ICAO_code>__.PTD
Note that there are at least two underscore characters between the ICAO code and the file
extension such that the length of the file name without the extension is six characters. Most ICAO
codes are four characters in length and thus have two underscore characters. Some ICAO codes,
however, can be shorter (e.g. F50) and thus require more underscore characters. For example, an
Airbus 310 which has the ICAO code of A310 is represented in BADA by the following files:
Operations Performance File:
A310__.OPF
Airline Procedures File:
A310__.APF
Performance Table File:
A310__.PTF
Performance Table Data:
A310__.PTD
The Fokker F50, which has the ICAO code of F50, is represented in BADA by the following files:
Operations Performance File:
F50____.OPF
Airline Procedures File:
F50____.APF
Performance Table File:
F50____.PTF
Performance Table Data:
F50____.PTD
All files belonging to BADA Revision 3.9, that is the Synonym Files, the GPF file and all APF, OPF,
PTF and PTD files, are controlled within a configuration management system. This system is
described in Section 6.2.
6.2. FILE CONFIGURATION MANAGEMENT
Starting with the BADA 3.4 release, the BADA Synonym Files, GPF and all APF, OPF, PTF and
PTD files are placed and managed under the Change Management Synergy (CM Synergy) tool at
EUROCONTROL.
This section briefly describes some of the CM Synergy features that will be used for the
management of the BADA files.
CM Synergy provides a complete change management environment in which development and
management of the files can be done easily, quickly, and securely. It maintains control of file
versions and allows management of project releases with some of the benefits listed below:
•
workflow management, which enables easy identification of the files modified to implement the
change, and review of the reason for a change,
•
project reproducibility by accurately creating baseline configurations,
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•
role-based security,
•
Distributed Change Management (DCM) which allows files sharing among any number of CM
Synergy databases. With DCM transfer of an entire database or a subset of a database can be
done, either automatically or manually.
The CM Synergy automated migration facilities feature complete version history migration from
RCS system archives. This has enabled to bring successfully all the BADA files with their history
under the CM Synergy control. A CM Synergy database is created for BADA project. Such a
database represents a data repository that stores all controlled data, including data files, their
properties and relationships to one another.
The following BADA files are placed in the CM Synergy database:
• the Synonym Files
• the GPF file
• all APF, OPF, PTF and PTD files
Within the CM Synergy, different methodologies in the way the files are managed are used. For
BADA database, the task-based methodology is chosen which enables the tracking of the changes
by using tasks, rather than individual files, as the basic unit of work.
The specific procedures used for configuration management are specified in the BADA
Configuration Management Manual [RD5].
6.2.1. File Identification
Any file managed in a CM Synergy database is uniquely identified by the following attributes: name,
version, type, and instance. By default, the four-part name (also called full name) is written like this:
name-version:type:instance.
A file name can be up to 151 characters long, and the version can be any 32-character
combination. The type can be any of the default types (e.g., csrc, ascii, etc.), or any BADA type that
is created (APF, OPF, PTF, PTD, GPF).
The name, version, and type are designated by the user, but the instance is calculated by CM
Synergy.
The version of a file corresponds to the evolution of the file in time. By default, CM Synergy creates
version numbers, starting with 1, for each file that is created in the CM Synergy database. Each
time the object is modified, CM Synergy increments the version.
The instance is used to distinguish between multiple objects with the same name and type, but that
are not versions of each other.
It is important to notice that, following the CM Synergy approach of the file identification, no
information on the file version is provided in the BADA file itself.
A new layout of the header of BADA files has been developed and it will be described in more
details in the following sections.
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6.2.2. History
The history of a file shows all the existing versions and the relationships between the versions. By
history, CM Synergy means all of the file versions created before the current file version (called
predecessors) and all of the file versions created after the current file version (called successors).
This functionality allows for the tracking of all modifications to a file.
6.2.3. Release
The release is a label that indicates the version of the project, in this case the release of BADA
files. BADA releases are usually identified by a two digit number, e.g. 3.3 or 3.4. However, the
name of release in CM Synergy can be made out of any combination of alphabetic and numerical
characters.
Like in the case of the file version, no information on the current BADA release is given in the
BADA files.
6.2.4.
Release Summary file
The ReleaseSummary file provides a list of all files delivered as part of the BADA release. It lists,
for each BADA file, the file name and BADA release identification, which is the BADA release in
which the file was last modified.
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6.3. SYNONYM FILE FORMAT
6.3.1. SYNONYM.LST File
The SYNONYM.LST file is an ASCII file which lists all aircraft types which are supported by the
BADA revision. An example of the SYNONYM.LST file is given below (partial listing).
CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC SYNONYM.LST CCCCCCCCCCCCCC/
CC
/
CC
BADA SYNONYM FILE
/
CC
/
CC
/
CC
File_name: SYNONYM.LST
/
CC
/
CC
Creation_date: Mar 26 2002
/
CC
/
CC
Modification_date: Mar 26 2002
/
CC
/
CC
/
CC====== Aircraft List ===============================================/
CC
/
CC
A/C
NAME OR MODEL
FILE
SYNONYMS
/
CC
CODE
/
CC
/
- A306__ AIRBUS A300B4-600
A306__
A306
- A30B__ AIRBUS A300B4-200
A30B__
A30B
IL76
- A310__ AIRBUS A310
A310__
A310
- A319__ AIRBUS A319
A319__
A319
- A320__ AIRBUS A320
A320__
A320
C17
- A321__ AIRBUS A321
A321__
A321
- A333__ AIRBUS A330-300
A333__
A333
A332
- A343__ AIRBUS A340-300
A343__
A343
A342
A345
A346
- AT43__ ATR ATR 42-300
AT43__
AT43
CN35
CVLT
AT44
- AT45__ ATR ATR 42-500
AT45__
AT45
- AT72__ ATR ATR 72
AT72__
AT72
A748
- ATP___ ADVANCED TURBOPROP
ATP___
ATP
G222
- B461__ BAE 146-100/RJ
B461__
B461
B462
B463
YK42
- B703__ BOEING 707-300
B703__
B703
B720
K35R
E3TF
E3CF
C135
VC10
IL62
- B722__ BOEING 727-100
B722__
B722
B721
BER4
- B732__ BOEING 737-228
B732__
B732
B731
A124
- B733__ BOEING 737-300
B733__
B733
- B734__ BOEING 737-400
B734__
B734
- B735__ BOEING 737-500
B735__
B735
B736
- B737__ BOEING 737-700
B737__
B737
There are three types of lines in the SYNONYM.LST file with the line type identified by the first two
characters in the line. These line types with their associated leading characters are listed below.
CC
comment line
CD
data line
synonym line
The data is organised into two blocks separated by a comment line consisting of the block name
and equal signs "=":
• file identification block
• aircraft list block
Each of these blocks is described in the subsections below.
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6.3.1.1. File Identification Block
The file identification block provides information on the file name, creation and modification date.
The block consists of 12 comment lines.
CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC SYNONYM.LST CCCCCCCCCCCCCC/
CC
/
CC
BADA SYNONYM FILE
/
CC
/
CC
/
CC
File_name: SYNONYM.LST
/
CC
/
CC
Creation_date: Mar 26 2002
/
CC
/
CC
Modification_date: Mar 26 2002
/
The comment lines specify the file name along with the creation and the modification date. The
creation date indicates the date when the file was created for the first time. The modification date
indicates when the contents of the file were last modified.
6.3.1.2. Aircraft Listing Block
The aircraft listing block consists of 5 comment lines with additional synonym lines for each aircraft
supported by the BADA Revision. A partial listing of this block is shown below.
CC====== Aircraft List ===============================================/
CC
/
CC
A/C
NAME OR MODEL
FILE
SYNONYMS
/
CC
CODE
/
CC
/
- A306__ AIRBUS A300B4-600
A306__
A306
- A30B__ AIRBUS A300B4-200
A30B__
A30B
IL76
- A310__ AIRBUS A310
A310__
A310
- A319__ AIRBUS A319
A319__
A319
- A320__ AIRBUS A320
A320__
A320
C17
- A321__ AIRBUS A321
A321__
A321
- A333__ AIRBUS A330-300
A333__
A333
A332
- A343__ AIRBUS A340-300
A343__
A343
A342
- AT43__ ATR ATR 42-300
AT43__
AT43
CN35
CVLT
AT44
- AT45__ ATR ATR 42-500
AT45__
AT45
- AT72__ ATR ATR 72
AT72__
AT72
A748
- ATP___ ADVANCED TURBOPROP
ATP___
ATP
G222
- B461__ BAE 146-100/RJ
B461__
B461
B462
B463
YK42
- B703__ BOEING 707-300
B703__
B703
B720
K35R
E3TF
E3CF
C135
VC10
IL62
- B722__ BOEING 727-100
B722__
B722
B721
BER4
- B732__ BOEING 737-228
B732__
B732
B731
A124
- B733__ BOEING 737-300
B733__
B733
- B734__ BOEING 737-400
B734__
B734
- B735__ BOEING 737-500
B735__
B735
B736
- B737__ BOEING 737-700
B737__
B737
There is one synonym line for each of the directly supported aircraft within the BADA release. Each
such line consists of 4 fields as described below:
(a)
Aircraft Code Field
This field identifies the aircraft type. It consists of a three or four-character ICAO code
followed by two or more underscore characters.
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(b)
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Name or Model Field
This field identifies the manufacturer and model of the aircraft.
(c)
File Name Field
This field identifies the file name for the APF, OPF, PTF or PTD files associated with the
aircraft (minus the file extension). For each aircraft this is the same as the A/C code.
(d)
Equivalence Field
This field lists any equivalences associated with the aircraft. By default, each aircraft has at
least one equivalence to itself.
Note that in some cases the name or model or equivalence fields may be continued onto the next
line as it is the case with the B703 model.
6.3.2. SYNONYM.NEW File
The SYNONYM.NEW file is an ASCII file, which lists all aircraft types, which are supported by the
BADA revision. Its format differs from the SYNONYM.LST file in that all supported aircraft are listed
alphabetically in the file whether they are supported directly or by equivalence. An example of the
SYNONYM.NEW file is given below (partial listing).
CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC SYNONYM.NEW CCCCCCCCCCCCCCC/
CC
/
CC
BADA SYNONYM FILE
/
CC
/
CC
/
CC
File_name: SYNONYM.NEW
/
CC
/
CC
Creation_date: Mar 26 2002
/
CC
/
CC
Modification_date: Mar 26 2002
/
CC
/
CC
/
CC====== Aircraft List ===============================================/
CC
/
CC
A/C
MANUFACTURER
NAME OR MODEL
FILE
OLD /
CC
CODE
CODE /
CC
/
CD * A10
FAIRCHILD
THUNDERBOLT II
FGTN__ A10A /
CD * A124
ANTONOV
ANTONOV AN-124
B732__ AN4R /
CD - A306
AIRBUS
A300B4-600
A306__ A306 /
CD - A30B
AIRBUS
A300B4-200
A30B__ A300 /
CD - A310
AIRBUS
A310
A310__ A310 /
CD - A319
AIRBUS
A319
A319__ A319 /
CD - A320
AIRBUS
A320
A320__ EA32 /
CD - A321
AIRBUS
A321
A321__ A321 /
CD * A332
AIRBUS
A330-200
A333__ A332 /
CD - A333
AIRBUS
A330-300
A333__ A330 /
CD * A342
AIRBUS
A340-200
A343__ A342 /
CD - A343
AIRBUS
A340-300
A343__ A340 /
CD * A345
AIRBUS
A340-500
A343__ A345 /
CD * A346
AIRBUS
A340-600
A343__ A346 /
CD * A4
MCDONNELL-DOUGLAS
SKYHAWK
FGTN__ A4
/
CD * A6
GRUMMAN
INTRUDER
FGTN__ EA6B /
CD * A748
BAE
BAE 748
AT72__ HN74 /
CD * AC80
ROCKWELL
TURBO COMMANDER
BE20__ AC6T /
CD * AC90
ROCKWELL
TURBO COMMANDER
BE20__ AC90 /
CD * AC95
ROCKWELL
TURBO COMMANDER
BE20__ AC95 /
CD * AJET
DASSAULT
ALPHA JET
FGTN__ AJET /
CD * AMX
EMBRAER
AMX
FGTN__ AMX /
CD * AN12
ANTONOV
AN-12
C130__ AN12 /
CD * AN24
ANTONOV
AN-124
F27___ AN24 /
CD * AN26
ANTONOV
AN-26
F27___ AN26 /
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There are three types of lines in the SYNONYM.NEW file with the line type identified by the first
two characters in the line. These line types with their associated two leading characters are listed
below.
CC
CD
FI
comment line
data line
end-of-file line
The data is organised into two blocks separated by a comment line consisting of the block name
and equal signs "=":
• file identification block
• aircraft list block
Each of these blocks is described in the subsections below.
6.3.2.1. File Identification Block
The file identification block provides information on the file name, creation and modification date.
The block consists of 12 comment lines as shown below.
CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC SYNONYM.NEW CCCCCCCCCCCCCCC/
CC
/
CC
BADA SYNONYM FILE
/
CC
/
CC
/
CC
File_name: SYNONYM.NEW
/
CC
/
CC
Creation_date: Mar 26 2002
/
CC
/
CC
Modification_date: Mar 26 2002
/
CC
/
The comment lines specify the file name along with the creation and last modification date. The
creation date indicates the date when the file was created for the first time. The modification date
indicates when the contents of the file were last modified.
6.3.2.2. Aircraft Listing Block
The aircraft listing block consists of 5 comment lines and at least one data line for each aircraft
supported by the BADA Revision. Some aircraft have more than one data line, see under (f). A
partial listing of this block is shown below.
CD
CD
CD
CD
*
*
-
A10
A124
A306
A30B
FAIRCHILD
ANTONOV
AIRBUS
AIRBUS
THUNDERBOLT II
ANTONOV AN-124
A300B4-600
A300B4-200
FGTN__
B732__
A306__
A30B__
A10A
AN4R
A306
A300
/
/
/
/
Each data line consists of 6 fields as described below:
(a)
Support Type Field
This field is one character in length being one of the following two values:
"-"
to indicate an aircraft type directly supported, and,
"*"
to indicate an aircraft type supported by equivalence with another directly
supported aircraft
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(b)
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Aircraft Code Field
This field identifies the aircraft type. It consists of a three or four-character ICAO code.
(c)
Manufacturer Field
This field identifies the manufacturer of the aircraft. Examples are Boeing, Airbus or Fokker.
(d)
Name or Model Field
This field identifies the name or model for the aircraft type. Examples are the 747-400
series or Learjet 35.
(e)
File Field
This field indicates the name of the OPF, APF, PTF or PTD file, which contains the
parameters for the aircraft type (minus the file extension).
For an aircraft type which is directly supported this file name will be the same as the ICAO
code with an additional two or more underscore characters to form a string of six characters
in length. For example, the file name corresponding to the A333 will be A333__. This
indicates an OPF file A333__.OPF, an APF file A333__.APF, a PTF file A333__.PTF and a
PTD file A333__.PTD. For the Fokker F-27 with an ICAO code of F27, the file names
include three underscore characters, that is, F27___.OPF, F27___.APF, F27___.PTF and
F27___.PTD.
For an aircraft type which is supported through equivalence the file name will indicate the
file for the equivalent aircraft type which should be used. As an example, the Antonov 12
(AN12) is equivalent to the Lockheed C-130 Hercules (C130). Thus the files C130__.OPF,
C130__.APF, C130__.PTF and C130__.PTD should be used.
(f)
Old Code field
The old code field gives the name of the aircraft that refers to the formerly known aircraft
designator as published in one of the previous editions of the ICAO document 8643 [RD10].
This allows the BADA 3.9 user to continue to use the old ICAO standard and to establish a
link between the old and the new aircraft designators.
The above fields are specified in the following fixed format (Fortran notation):
'CD', 1X, A1, 1X, A4, 3X, A18, 1X, A25, 1X, A6, 2X, A4
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6.3.3. SYNONYM_ALL.LST File
The SYNONYM_ALL.LST file is an ASCII file, which lists all aircraft types, which are supported by
the BADA revision. Like in the SYNONYM.NEW file, all supported aircraft are listed alphabetically
in the file whether they are supported directly or by equivalence. An example of the
SYNONYM_ALL.LST file is given below (partial listing).
CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC SYNONYM_ALL.LST CCCCCCCCCCCCCCC/
CC
/
CC
BADA SYNONYM_ALL FILE
/
CC
/
CC
/
CC
File_name: SYNONYM_ALL.LST
/
CC
/
CC
Creation_date: May 22 2003
/
CC
/
CC
Modification_date: May 22 2003
/
CC
/
CC
/
CC
/
CC====================================================================/
CC
/
CC
/
CC
ICAO
ICAO
ICAO
CC
A/C
NAME OR MODEL
MANUFACTURER FILE
CODE
CODE
CODE
CC
BADA 3.5
V24
V25
V26
CC
CD * A10
THUNDERBOLT II
FAIRCHILD
FGTN__
A10A
A10
A10
CD * A124
ANTONOV AN-124
ANTONOV
B732__
AN4R
A124
A124
CD - A306
A300B4-600
AIRBUS
A306__
A306
A306
A306
CD - A30B
A300B4-200
AIRBUS
A30B__
EA30
A300
A30B
CD - A310
A310
AIRBUS
A310__
EA31
A310
A310
CD * A318
A318
AIRBUS
A319__
A318
A318
A318
CD - A319
A319
AIRBUS
A319__
A319
A319
A319
CD - A320
A320
AIRBUS
A320__
EA32
A320
A320
CD - A321
A321
AIRBUS
A321__
A321
A321
A321
CD - A332
A330-200
AIRBUS
A332__
A332
A332
A332
CD - A333
A330-300
AIRBUS
A333__
EA33
EA33
EA33
CD * A342
A340-200
AIRBUS
A343__
A342
A342
A342
CD - A343
A340-300
AIRBUS
A343__
EA34
EA34
EA34
CD * A345
A340-500
AIRBUS
A343__
A345
A345
A345
CD * A346
A340-600
AIRBUS
A343__
A346
A346
A346
ICAO
CODE
V27
ICAO
CODE
V28
ICAO
CODE
V29
ICAO
CODE
V30
A10
A124
A306
A30B
A310
A318
A319
A320
A321
A332
A330
A342
A340
A345
A346
A10
A124
A306
A30B
A310
A318
A319
A320
A321
A332
A333
A342
A343
A345
A346
A10
A124
A306
A30B
A310
A318
A319
A320
A321
A332
A333
A342
A343
A345
A346
A10
A124
A306
A30B
A310
A318
A319
A320
A321
A332
A333
A342
A343
A345
A346
There are three types of lines in the SYNONYM_ALL.LST file with the line type identified by the
first two characters in the line. These line types with their associated two leading characters are
listed below.
CC
CD
FI
comment line
data line
end-of-file line
The data is organised into two blocks separated by a comment line consisting of equal signs "=":
• file identification block
• aircraft list block
Each of these blocks is described in the subsections below.
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6.3.3.1. File Identification Block
The file identification block provides information on the file name, creation and modification date.
The block consists of 13 comment lines as shown below.
CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC SYNONYM_ALL.LST CCCCCCCCCCCCCCC/
CC
/
CC
BADA SYNONYM_ALL FILE
/
CC
/
CC
/
CC
File_name: SYNONYM.NEW
/
CC
/
CC
Creation_date: May 22 2003
/
CC
/
CC
Modification_date: May 22 2003
/
CC
/
The comment lines specify the file name along with the creation and last modification date. The
creation date indicates the date when the file was created for the first time. The modification date
indicates when the contents of the file were last modified.
6.3.3.2. Aircraft Listing Block
The aircraft listing block consists of 7 comment lines and at least one data line for each aircraft
supported by the BADA Revision. Some aircraft have more than one data line, see under (f). A
partial listing of this block is shown below.
*
*
-
A10
A124
A306
A30B
THUNDERBOLT II
ANTONOV AN-124
A300B4-600
A300B4-200
FAIRCHILD
ANTONOV
AIRBUS
AIRBUS
FGTN__
B732__
A306__
A30B__
A10A
AN4R
A306
EA30
A10
A124
A306
A300
A10
A124
A306
A30B
A10
A124
A306
A30B
A10
A124
A306
A30B
A10
A124
A306
A30B
A10
A124
A306
A30B
Each data line consists of 5 fields describing the aircraft type and number of additional fields
providing the history of ICAO aircraft type designators. Detailed description is given below:
(a)
Support Type Field
This field is one character in length being one of the following two values:
(b)
"-"
to indicate an aircraft type directly supported, and,
"*"
to indicate an aircraft type supported by equivalence with another directly supported
aircraft
Aircraft Code Field
This field identifies the aircraft type. It consists of a three or four-character ICAO code.
(c)
Manufacturer Field
This field identifies the manufacturer of the aircraft. Examples are Boeing, Airbus or Fokker.
(d)
Name or Model Field
This field identifies the name or model for the aircraft type. Examples are the 747-400
series or Learjet 35.
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(e)
File Field
This field indicates the name of the OPF, APF, PTF or PTD file, which contains the
parameters for the aircraft type (minus the file extension).
For an aircraft type which is directly supported this file name will be the same as the ICAO
code with an additional two or more underscore characters to form a string of six characters
in length. For example, the file name corresponding to the A333 will be A333__. This
indicates an OPF file A333__.OPF, an APF file A333__.APF, a PTF file A333__.PTF and a
PTD file A333__.PTD. For the Fokker F-27 with an ICAO code of F27, the file names
include three underscore characters, that is, F27___.OPF, F27___.APF, F27___.PTF and
F27___.PTD.
For an aircraft type which is supported through equivalence the file name will indicate the
file for the equivalent aircraft type which should be used. As an example, the Antonov 12
(AN12) is equivalent to the Lockheed C-130 Hercules (C130). Thus the files C130__.OPF,
C130__.APF, C130__.PTF and C130__.PTD should be used.
(f)
Old Code fields
The old code fields give the name of the aircraft that refers to the formerly known aircraft
designator as published in one of the previous editions (versions, i.e. V24 to V37) of the
ICAO document 8643 [RD10]. This allows the BADA 3.9 user to continue to use the old
ICAO standard and to establish a link between the old and the new aircraft designators, as
well as the corresponding aircraft file name from the most recent BADA release. If the
specific aircraft model version did not have an assigned designator in the past editions of
the ICAO document or the information was not available to the BADA team, then the most
recent designator is used throughout all the versions.
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6.4. OPF FILE FORMAT
The Operations Performance File (OPF) is an ASCII file, which for a particular aircraft type
specifies the operations performance parameters described in Section 3. An example of an OPF
file for the A306 (Airbus 300B4-600) aircraft is shown below.
CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC A306__.OPF CCCCCCCCCCCCCC/
CC
/
CC
AIRCRAFT PERFORMANCE OPERATIONAL FILE
/
CC
/
CC
/
CC
File_name: A306__.OPF
/
CC
/
CC
Creation_date: Mar 26 2002
/
CC
/
CC
Modification_date: Mar 26 2002
/
CC
/
CC
/
CC====== Actype ======================================================/
CD
A306__
2 engines
Jet
H
/
CC
Airbus A300-B4-622 with PW4158 engines
wake
/
CC
/
CC====== Mass (t) ====================================================/
CC
reference
minimum
maximum
max payload mass grad /
CD
.14000E+03
.87000E+02
.17170E+03
.39000E+02
.14100E+00 /
CC====== Flight envelope =============================================/
CC
VMO(KCAS)
MMO
Max.Alt
Hmax
temp grad /
CD
.33500E+03
.82000E+00
.41000E+05
.31600E+05 -.67000E+02 /
CC====== Aerodynamics ================================================/
CC Wing Area and Buffet coefficients (SIM)
/
CCndrst Surf(m2)
Clbo(M=0)
k
CM16
/
CD 5
.26000E+03
.15300E+01
.10290E+01
.00000E+00
/
CC
Configuration characteristics
/
CC n Phase Name
Vstall(KCAS)
CD0
CD2
unused
/
CD 1 CR
Clean
.15100E+03
.19000E-01
.53000E-01
.00000E+00 /
CD 2 IC
S15F00
.11700E+03
.33057E-01
.45362E-01
.00000E+00 /
CD 3 TO
S15F00
.11700E+03
.33057E-01
.45362E-01
.00000E+00 /
CD 4 AP
S15F15
.10900E+03
.38031E-01
.44932E-01
.00000E+00 /
CD 5 LD
S30F40
.97000E+02
.78935E-01
.44822E-01
.00000E+00 /
CC
Spoiler
/
CD 1
RET
/
CD 2
EXT
.00000E+00
.00000E+00 /
CC
Gear
/
CD 1
UP
/
CD 2
DOWN
.22500E-01
.00000E+00
.00000E+00 /
CC
Brakes
/
CD 1
OFF
/
CD 2
ON
.00000E+00
.00000E+00 /
CC====== Engine Thrust ===============================================/
CC
Max climb thrust coefficients (SIM)
/
CD
.30400E+06
.44800E+05
.11600E-09
.67500E+01
.42600E-02 /
CC
Desc(low)
Desc(high)
Desc level
Desc(app)
Desc(ld) /
CD
.73000E-02
.20600E-01
.80000E+04
.12000E+00
.36000E+00 /
CC
Desc CAS
Desc Mach
unused
unused
unused
/
CD
.28000E+03
.79000E+00
.00000E+00
.00000E+00
.00000E+00 /
CC====== Fuel Consumption ============================================/
CC
Thrust Specific Fuel Consumption Coefficients
/
CD
.88100E+00
.16900E+05
/
CC
Descent Fuel Flow Coefficients
/
CD
.26805E+02
.45700E+05
/
CC
Cruise Corr.
unused
unused
unused
unused
/
CD
.10380E+01
.00000E+00
.00000E+00
.00000E+00
.00000E+00 /
CC====== Ground ======================================================/
CC
TOL
LDL
span
length
unused
/
CD
.23620E+04
.15550E+04
.44840E+02
.54080E+02
.00000E+00 /
CC====================================================================/
FI
/
There are three types of lines in the OPF file with the line type identified by the first two characters
in the line. These line types with their associated two leading characters are listed below.
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CC
comment line
CD
FI
data line
end-of-file line
The comment lines are provided solely for the purpose of improving the readability of the file. All
coefficients are contained within the CD lines in a fixed format. The end-of-file line is included as
the last line in the file in order to facilitate the reading of the file in certain computing environments.
The data is organised into a total of eight blocks with each block separated by a comment line
containing the block name and equal signs "=". These blocks are listed below and are described in
further detail in the subsections below.
•
•
•
•
•
•
•
•
file identification block
aircraft type block
mass block
flight envelope block
aerodynamics block
engine thrust block,
fuel consumption block
ground movements block
6.4.1. File Identification Block
The file identification block provides information on the file name, creation date and modification
date. The block consists of 11 comment lines. An example of the file identification block for the
A306__.OPF file is shown below.
CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC A306__.OPF CCCCCCCCCCCCCC/
CC
/
CC
AIRCRAFT PERFORMANCE OPERATIONAL FILE
/
CC
/
CC
/
CC
File_name: A306__.OPF
/
CC
/
CC
Creation_date: Mar 26 2002
/
CC
/
CC
Modification_date: Mar 26 2002
/
CC
/
The comment lines specify the file name along with the creation date and last modification date.
The creation date indicates the date when the file was created for the first time. The modification
date indicates when the contents of the file were last modified.
6.4.2. Aircraft Type Block
The OPF aircraft type block consists of 1 data line with 3 comment lines for a total of 4 lines. An
example of the aircraft type block is given below.
1 ->
50
CC====== Actype ======================================================/
CD
A306__
2 engines
Jet
H
/
CC
Airbus A300-B4-622 with PW4158 engines
wake
/
CC
/
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The data line specifies the following aircraft type parameters:
• ICAO aircraft code (followed by 2 or more underscore characters as required to form a
six character string)
• number of engines, neng
• engine type
• wake category
The engine type can be one of the following three values: Jet, Turboprop or Piston. The wake
category can be one of the four values J (jumbo), H (heavy), M (medium) or L (light).
The four values are specified in the following fixed format (Fortran notation)
'CD', 2X, A6, 10X, I1, 12X, A9, 17X, A1
The comment lines typically indicate the engine manufacturer's designation and the source of the
performance coefficients.
6.4.3. Mass Block
The OPF mass block consists of 1 data line with 2 comment lines for a total of 3 lines.
An example of the mass block is given below.
1 ->
CC====== Mass (t) ====================================================/
CC
reference
minimum
maximum
max payload mass grad /
CD
.14000E+03
.87000E+02
.17170E+03
.39000E+02
.14100E+00 /
The data line specifies the following BADA mass model parameters:
mref
mmin
mmax
mpyld
Gw
These parameters are specified in the following fixed format (Fortran notation)
'CD', 2X, 5 (3X, E10.5)
6.4.4. Flight Envelope Block
The OPF flight envelope block consists of 1 data line with 2 comment lines for a total of 3 lines. An
example of the flight envelope block is given below.
1 ->
CC====== Flight envelope =============================================/
CC
VMO(KCAS)
MMO
Max.Alt
Hmax
temp grad /
CD
.33500E+03
.82000E+00
.41000E+05
.31600E+05 -.67000E+02 /
The date line specifies the following BADA speed envelope parameters:
VMO
MMO
hMO
hmax
Gt
Note that all altitudes are expressed in feet.
These parameters are specified in the following fixed format (Fortran notation):
'CD', 2X, 5 (3X, E10.5)
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6.4.5. Aerodynamics Block
The OPF aerodynamics block consists of 12 data lines and 8 comment lines for a total of 20 lines.
An example of the aerodynamics block is given below.
1 ->
2
3
4
5
6
->
->
->
->
->
7 ->
8 ->
9 ->
10 ->
12 ->
13 ->
CC====== Aerodynamics ================================================/
CC Wing Area and Buffet coefficients (SIM)
/
CCndrst Surf(m2)
Clbo(M=0)
k
CM16
/
CD 5
.26000E+03
.15300E+01
.10290E+01
.00000E+00
/
CC
Configuration characteristics
/
CC n Phase Name
Vstall(KCAS)
CD0
CD2
unused
/
CD 1 CR
Clean
.15100E+03
.19000E-01
.53000E-01
.00000E+00 /
CD 2 IC
S15F00
.11700E+03
.33057E-01
.45362E-01
.00000E+00 /
CD 3 TO
S15F00
.11700E+03
.33057E-01
.45362E-01
.00000E+00 /
CD 4 AP
S15F15
.10900E+03
.38031E-01
.44932E-01
.00000E+00 /
CD 5 LD
S30F40
.97000E+02
.78935E-01
.44822E-01
.00000E+00 /
CC
Spoiler
/
CD 1
RET
/
CD 2
EXT
.00000E+00
.00000E+00 /
CC
Gear
/
CD 1
UP
/
CD 2
DOWN
.2250E-01
.00000E+00
.00000E+00 /
CC
Brakes
/
CD 1
OFF
/
CD 2
ON
.00000E+00
.00000E+00 /
The first data line specifies the following BADA aerodynamic model parameters:
S
Clbo(M=0)
k
CM16
These parameters are specified in the following fixed format (Fortran notation):
'CD', 2X, 4 (3X, E10.5)
Note that the "5" under the header "ndrst" stands for the five drag settings. Currently this is not
used but is left in for compatibility requirements.
The next line holds besides the stall speed and flap setting for cruise as well as the values for the
two drag coefficients for this configuration:
(Vstall)CR
CD0
CD2
These parameters are specified in the following fixed format (Fortran notation):
'CD', 15X, 3 (3X, E10.5)
The next four data lines have the same format and correspond to the other configurations. The
configurations are specified in the following order, corresponding to a semi-monotonically
decreasing stall speed:
IC
initial climb
TO
take-off
AP
approach
LD
landing
The stall speed, (Vstall)i, is specified for each configuration, and CD0 and CD2 are given if available in
the following fixed format (Fortran notation):
'CD', 15X, 3 (3X, E10.5)
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In case the IC configuration is equal to the CR configuration, the values for CD0 and CD2 are
mentioned only in the CR dataline. Note that CD0 and CD2 coefficients for IC and TO configurations
are not used but are included for the reason of compatibility with previous versions.
The data lines 7 through 9 are not used but are included for the reason of compatibility with
previous versions.
Dataline 10 holds the drag increment for landing gear down:
CD0,∆LDG
The format of this line is:
'CD', 31X, E10.5
Datalines 11 and 12 are not used but are included for the reason of compatibility with previous
versions.
6.4.6. Engine Thrust Block
The OPF engine thrust block consists of 3 data lines with 4 comment lines for a total of 7 lines. An
example of the engine thrust block is given below.
1 ->
2 ->
3 ->
CC====== Engine Thrust ===============================================/
CC
Max climb thrust coefficients (SIM)
/
CD
.30400E+06
.44800E+05
.11600E-09
.67500E+01
.42600E-02 /
CC
Desc(low)
Desc(high)
Desc level
Desc(app)
Desc(ld) /
CD
.73000E-02
.20600E-01
.80000E+04
.12000E+00
.36000E+00 /
CC
Desc CAS
Desc Mach
unused
unused
unused
/
CD
.28000E+03
.79000E+00
.00000E+00
.00000E+00
.00000E+00 /
The first data line specifies the following BADA parameters used to calculate the maximum climb
thrust, that is:
CTc,1
CTc,2
CTc,3
CTc,4
CTc,5
These parameters are specified in the following fixed format (Fortran notation):
'CD', 2X, 5 (3X, E10.5)
The second data line specifies the following BADA parameters used to calculate cruise and
descent thrust, that is:
CTdes,low
CTdes,high
Hp,des
CTdes,app
CTdes,ld
These parameters are specified in the following fixed format (Fortran notation):
'CD', 2X, 5 (3X, E10.5)
Note that the CTdes,app and CTdes,ld coefficients are determined in order to obtain a 3° descent
gradient during approach and landing.
The third data line specifies the reference speeds during descent, that is:
Vdes,ref
Mdes,ref
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EUROCONTROL
These parameters are specified in the following fixed format (Fortran notation):
'CD', 2X, 2 (3X, E10.5)
Note that these two parameters are no longer used in BADA model implementation, but are left in
place only to provide information on one of the reference speeds during descent used during the
model identification.
The zero values at the end of this data line are not used but are included in the file due to
compatibility requirements with previous versions.
6.4.7. Fuel Consumption Block
The OPF fuel consumption block consists of 3 data lines with 4 comment lines for a total of 7 lines.
An example of a fuel consumption block is shown below.
1 ->
2 ->
3 ->
CC====== Fuel Consumption ============================================/
CC
Thrust Specific Fuel Consumption Coefficients
/
CD
.88100E+00
.16900E+05
/
CC
Descent Fuel Flow Coefficients
/
CD
.26805E+02
.45700E+05
/
CC
Cruise Corr.
unused
unused
unused
unused
/
CD
.10380E+01
.00000E+00
.00000E+00
.00000E+00
.00000E+00 /
The first data line specifies the following BADA parameters for thrust specific fuel consumption.
Cf1
Cf2
These parameters are specified in the following fixed format (Fortran notation):
'CD', 2X, 2 (3X, E10.5)
The second data line specifies the following BADA parameters for descent fuel flow.
Cf3
Cf4
These parameters are specified in the following fixed format (Fortran notation):
'CD', 2X, 2 (3X, E10.5)
The third data line specifies the cruise fuel flow correction factor.
Cfcr
The parameter is specified in the following fixed format (Fortran notation):
'CD', 5X, E10.5
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EUROCONTROL
6.4.8. Ground Movement Block
The OPF ground movement block consists of 1 data line with 3 comment lines for a total of 4 lines.
An example of a ground movement block is shown below. The ground movement block is the last
block in the OPF file and is thus followed by the end-of-file line as shown below.
1 ->
CC====== Ground ======================================================/
CC
TOL
LDL
span
length
unused
/
CD
.23620E+04
.15550E+04
.44840E+02
.54080E+02
.00000E+00 /
CC====================================================================/
FI
/
The data line specifies the following BADA parameters for ground movements:
TOL
LDL
span
length
These parameters are specified in the following fixed format (Fortran notation):
'CD', 2X, 4 (3X, E10.5)
6.5. APF FILE FORMAT
The Airlines Procedures File (APF) is an ASCII file which, for a particular aircraft type, specifies
recommended speed procedures for climb, cruise, and descent conditions. An example of an APF
file for the Airbus A306 aircraft is shown below.
CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC A306__.APF CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC/
CC
/
CC
AIRLINES PROCEDURES FILE
/
CC
/
CC
File_name: A306__.APF
/
CC
/
CC
Creation_date: Mar 26 2002
/
CC
/
CC
Modification_date: Mar 26 2002
/
CC
/
CC
/
CC
/
CC
LO= 087.00 to ---.-- / AV= ---.-- to ---.-- / HI= ---.-- to 171.70
/
CC
/
CC=================================================================================================/
CC COM CO
Company name ------climb------- --cruise-- -----descent------ --approach- model- /
CC
mass lo hi
lo hi
hi lo
(unused)
/
CC
version engines ma cas cas mc xxxx xx cas cas mc mc cas cas xxxx xx xxx xxx xxx opf___ /
CC===:=======:=======::==::===:===:==:====:==::===:===:==::==:===:===:====:==::===:===:===::======:/
CD *** **
Default Company
/
CD
B4_622 PW4158
LO 250 300 79
250 310 79 79 280 250
0
0
0 A306__ /
CD
B4_622 PW4158
AV 250 300 79
250 310 79 79 280 250
0
0
0 A306__ /
CD
B4_622 PW4158C HI 250 300 79
250 310 79 79 280 250
0
0
0 A306__ /
CC===:=======:=======::==::===:===:==:====:==::===:===:==::==:===:===:====:==::===:===:===::======:/
CC////////////////////////////////// THE END
////////////////////////////////////////////////////
There are two types of lines in the APF file with the line type identified by the first two characters in
the line. These line types with their associated two leading characters are listed below:
CC
CD
- comment line
- data line
The last line in the file, as shown above, is also a comment line.
The comment lines are provided solely for the purpose of improving the readability of the file. All
coefficients are contained within the CD lines in a fixed format.
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The data is organised into 2 blocks separated by a comment line containing a string of equal signs,
"=":
• file identification block
• speed procedures block
Each of the two blocks is described further in the subsections below.
6.5.1. File Identification Block
The file identification block provides information on the file name, creation date and modification
date. The block consists of 14 comment lines. An example of a file identification block is shown
below.
CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC A306__.APF CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC/
CC
/
CC
AIRLINES PROCEDURES FILE
/
CC
/
CC
File_name: A306__.APF
/
CC
/
CC
Creation_date: Mar 26 2002
/
CC
/
CC
Modification_date: Mar 26 2002
/
CC
/
CC
/
CC
/
CC
LO= 087.00 to ---.-- / AV= ---.-- to ---.-- / HI= ---.-- to 171.70
/
CC
/
The comment lines provide background information on the file contents. In addition, the comment
lines specify the file name along with the creation and last modification date. The creation date
indicates the date when the file was created for the first time. The modification date indicates when
the contents of the file were last modified.
The second last comment line in the identification block specifies three mass ranges for the aircraft
in tonnes. That is, a low range (LO), average range (AV) and high range (HI). The definition of
these ranges is used for interpreting the information presented below in the procedures
specification block. In the example given above, all three ranges are assumed equivalent.
6.5.2. Procedures Specification Block
The APF procedures specification block consists of 4 data lines with 7 comment lines for a total of
11 lines. An example of a procedures specification block is shown below.
1
2
3
4
->
->
->
->
CC=================================================================================================/
CC COM CO
Company name ------climb------- --cruise-- -----descent------ --approach- model- /
CC
mass lo hi
lo hi
hi lo
(unused)
/
CC
version engines ma cas cas mc xxxx xx cas cas mc mc cas cas xxxx xx xxx xxx xxx opf___ /
CC===:=======:=======::==::===:===:==:====:==::===:===:==::==:===:===:====:==::===:===:===::======:/
CD *** **
Default Company
/
CD
B4_622 PW4158
LO 250 300 79
250 310 79 79 280 250
0
0
0 A306__ /
CD
B4_622 PW4158
AV 250 300 79
250 310 79 79 280 250
0
0
0 A306__ /
CD
B4_622 PW4158C HI 250 300 79
250 310 79 79 280 250
0
0
0 A306__ /
CC===:=======:=======::==::===:===:==:====:==::===:===:==::==:===:===:====:==::===:===:===::======:/
CC////////////////////////////////// THE END
////////////////////////////////////////////////////
56
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EUROCONTROL
The first data line specifies the company name for which the next three datalines are valid. The
company can be identified by its 3 and 2 letter code plus the company name. The dataline fomat is:
'CD', 2X, A3, 1X, A2, 4X, A15
As it is, within BADA all APF files specify procedures for only one "default" company.
The next three data lines specify the following parameters corresponding to climb, cruise and
descent:
Vcl,1
Vcl,2
Mcl
Vcr,1
Vcr,2
Mcr
Mdes
Vdes,2
Vdes,1
Note that all Mach number values are also multiplied by a value of 100. For example, the 78
indicated for Mcl above corresponds to a Mach number of 0.78.
The three lines specify parameters for mass ranges of Low (LO), Average (AV) and High (HI)
respectively. These parameters are specified in the following fixed format (Fortran notation):
'CD', 25X, 2(I3, 1X), I2, 10X, 2(I3, 1X), I2, 2X, I2, 2(1X, I3)
Note that approach values are set to zero. These values are not used but are included in the file
due to compatibility requirements with previous versions.
Also, each line specifies an aircraft version number, engine, and operational model. The
operational model is always the same as the file name. The version number may provide some
additional information on the aircraft version covered by the file while the engine states which
engine is used by the aircraft.
The file format is designed such that the four data lines can be repeated for the different
companies which operate the aircraft and which may have different standard procedures. If data
were to be provided for more than one company then the version, engine and operational model
fields may be useful since different companies could operate different versions of the aircraft with
different engines and thus different associated operational models.
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6.6. PTF FILE FORMAT
The Performance Table File (PTF) is an ASCII file, which for a particular aircraft type specifies
cruise, climb and descent performance at different flight levels. An example of a PTF file for the
Airbus A306 aircraft is shown below.
BADA PERFORMANCE FILE
Apr 23 2002
AC/Type: A306
Source OPF File:
Source APF file:
Mar 26 2002
Mar 26 2002
Speeds:
CAS(LO/HI) Mach
Mass Levels [kg]
Temperature:
ISA
climb
- 250/300
0.79
low
- 104400
cruise - 250/310
0.79
nominal - 140000
Max Alt. [ft]: 41000
descent - 250/280
0.79
high
- 171700
=======================================================================================
FL |
CRUISE
|
CLIMB
|
DESCENT
| TAS
fuel
| TAS
ROCD
fuel
| TAS ROCD
fuel
| [kts]
[kg/min]
| [kts]
[fpm]
[kg/min] | [kts] [fpm] [kg/min]
|
lo
nom
hi
|
lo nom
hi
nom
|
nom
nom
=======================================================================================
0 |
| 157
2210 1990 1620
270.3 | 131
760
97.2
|
|
|
5 |
| 158
2190 1970 1600
267.3 | 132
780
96.1
|
|
|
10 |
| 159
2170 1950 1570
264.3 | 138
800
95.0
|
|
|
15 |
| 166
2290 2030 1650
261.5 | 149
850
94.0
|
|
|
20 |
| 167
2270 2010 1620
258.5 | 181 1020
31.0
|
|
|
30 | 230
61.2 81.4 104.3 | 190
2750 2360 1920
253.0 | 230 1360
25.0
|
|
|
40 | 233
61.2 81.4 104.4 | 225
3350 2780 2270
247.7 | 233 1380
24.5
|
|
|
60 | 272
65.9 81.7 99.6 | 272
4210 3070 2370
236.8 | 240 1410
23.3
|
|
|
80 | 280
65.8 81.7 99.7 | 280
4040 2930 2230
225.7 | 280 1550
22.1
|
|
|
100 | 289
65.8 81.7 99.8 | 289
3860 2780 2090
214.8 | 289 1590
20.9
|
|
|
120 | 297
65.7 81.7 99.8 | 356
3820 2800 2170
204.8 | 332 1880
19.8
|
|
|
140 | 306
65.6 81.7 99.9 | 366
3590 2610 2000
194.3 | 342 1920
18.6
|
|
|
160 | 389
82.4 93.1 105.3 | 377
3360 2410 1820
184.1 | 353 1960
17.4
|
|
|
180 | 401
82.1 92.9 105.1 | 388
3120 2220 1650
174.2 | 363 2000
16.2
|
|
|
200 | 413
81.7 92.6 104.9 | 400
2880 2020 1470
164.5 | 375 2040
15.1
|
|
|
220 | 425
81.3 92.3 104.7 | 412
2630 1810 1290
155.0 | 386 2080
13.9
|
|
|
240 | 438
80.9 91.9 104.5 | 425
2380 1610 1100
145.8 | 398 2120
12.7
|
|
|
260 | 452
80.4 91.6 104.3 | 438
2130 1400 920
136.9 | 411 2160
11.6
|
|
|
280 | 466
79.9 91.2 104.1 | 452
1880 1200 730
128.1 | 424 2200
10.4
|
|
|
290 | 468
78.4 90.1 103.4 | 459
1760 1090 640
123.9 | 431 2220
9.8
|
|
|
310 | 464
74.3 87.0 101.5 | 464
2200 1290 660
115.4 | 444 2250
8.6
|
|
|
330 | 459
70.6 84.7 100.6 | 459
1950 1050 420
107.2 | 459 2290
7.4
|
|
|
350 | 455
67.6 83.0 97.9 | 455
1700 810 170
99.2 | 455 3150
6.3
|
|
|
370 | 453
65.1 82.0 90.3 | 453
1320 510
0
91.6 | 453 2850
5.1
|
|
|
390 | 453
63.2 81.9 83.0 | 453
1080 260
0
84.1 | 453 2850
3.9
|
|
|
410 | 453
61.9 75.9 75.9 | 453
830
10
0
77.0 | 453 2880
2.8
=====================================================================================
58
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EUROCONTROL
The OPF and APF files are generated as a result of a modelling process using MatLab [RD6].
Once these two files are generated, the PTF can be automatically generated. A brief summary of
the format of these files is given below.
The header of each PTF file contains information as described below.
file creation date:
This is in the first line, at the top-right corner
aircraft type:
This is in the third line.
source file dates:
The last modification dates of the OPF and APF files which were used to
create the PTF file are given in the 4th and 5th lines respectively.
speeds:
The speed laws for climb, cruise and descent are specified in lines 8, 9 and
10, that is:
climb
cruise
descent
mass Levels:
min(Vcl,1, 250kt) / Vcl,2
min(Vcr,1, 250kt) / Vcr,2
min(Vdes,1, 250kt) / Vdes,2
Mcl
Mcr
Mdes
The performance tables provide data for three different mass levels in lines
8, 9 and 10, that is:
low
nominal
high
1.2 mmin.
mref
mmax
Note that the low mass is not the minimum mass but 1.2 times the
minimum mass.
Temperature data:
The temperature is mentioned in line 7. All PTF files currently provide data
for ISA conditions only.
Maximum altitude:
The maximum altitude as specified in the OPF file, hMO, is given in line 9.
The table of performance data within the file consists of 13 columns. Each of these columns is
described below:
Column 1
Column 2
Column 3
Column 4
Column 5
Column 6
Column 7
Column 8
Column 9
Column 10
Column 11
Column 12
Column 13
FL
cruise TAS (nominal mass) [knots]
cruise fuel consumption (low mass) [kg/min]
cruise fuel consumption (nominal mass) [kg/min]
cruise fuel consumption (high mass) [kg/min]
climb TAS (nominal mass) [knots]
rate of climb with reduced power (low mass) [ft/min]
rate of climb with reduced power (nominal mass) [ft/min]
rate of climb with reduced power (high mass) [ft/min]
climb fuel consumption (nominal mass) [kg/min]
descent TAS (nominal mass) [knots]
rate of descent (nominal mass) [ft/min]
descent fuel consumption (nominal mass) [kg/min]
The format for data presented in each line of the table is as follows (Fortran notation).
I3, 4X, I3, 2X, 3(1X, F5.1), 5X, I3, 2X, 3(1X, I5), 3X, F5.1, 5X, I3, 2X, I5, 3X, F4.1
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
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User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
Further explanatory notes on the data presented in the performance tables are given below:
(a)
Cruise data is only specified for flight levels greater than or equal to 30.
(b)
Performance data is specified up to a maximum flight level of 510 or to highest level for
which a positive rate of climb can be achieved at the low mass.
(c)
True airspeed for climb, cruise and descent is determined based on the speed schedules
specified in Sections 4.1, 4.2 and 4.3 respectively.
(d)
Rates of climb are calculated at each flight level assuming the energy share factors
associated with constant CAS or constant Mach speed laws and using the reduced power
correction as given in Section 3.8.
(e)
The fuel consumption in climb is independent of the aircraft mass and thus only one value
is given. There are three different climb rates however corresponding to low, nominal and
high mass conditions.
(f)
The rate of descent and fuel consumption in descent is calculated assuming the nominal
mass. Values for other mass conditions are not given.
(g)
Discontinuities in climb rate can occur for the following reasons:
• change in speed between flight levels (e.g. removal of 250 kt restriction above
FL100),
• transition from constant CAS to constant Mach (typically around FL300),
• transition through the tropopause (FL360 for ISA),
• end of the application scope for reduced climb power (at 80% of hmax).
(h)
Discontinuities in descent rate can occur for the following reasons:
•
•
•
•
•
transition through tropopause (FL360 for ISA),
transition from constant Mach to constant CAS,
change in assumed descent thrust (specified by the BADA hdes parameter),
change to approach or landing aerodynamic configuration,
change in speed between flight levels (e.g. application of 250 kt limit below FL100).
(i)
The PTF files are made with "non-clean" configuration data for approach and landing when
such data is available (see Section 3.6.1).
(j)
The performance data presented in the table are computed by using ‘point type’ calculation,
that is without performing integration over time: aircraft weight is constant and does not
account for consumed fuel, and speed changes take place immediately.
(k)
The flight envelope limitations are not taken into account for calculation of performance
parameters8
Note that all PTF files are available in document form in [RD9].
8 Example: cruise fuel flow is calculated without checking, for given aircraft weight, speed and FL, that aircraft drag is lower than
maximum available cruise thrust.
60
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
FL[-]
0
5
10
15
20
30
40
60
80
100
120
140
160
180
200
220
240
260
280
290
310
330
350
370
390
410
T[K] p[Pa] rho[kg/m3] a[m/s] TAS[kt] CAS[kt]
288 101325
1.225
340
136.35
136.35
287 99508
1.207
340
137.34
136.35
286 97717
1.190
339
138.34
136.35
285 95952
1.172
339
144.45
141.35
284 94213
1.155
338
145.51
141.35
282 90812
1.121
337
168.52
161.35
280 87511
1.088
336
202.72
191.35
276 81200
1.024
333
272.30
250.00
272 75262
0.963
331
280.34
250.00
268 69682
0.905
328
345.37
300.00
264 64441
0.849
326
355.51
300.00
260 59524
0.796
324
366.04
300.00
256 54915
0.746
321
376.97
300.00
252 50600
0.698
319
388.32
300.00
249 46563
0.653
316
400.10
300.00
245 42791
0.610
314
412.32
300.00
241 39271
0.569
311
425.00
300.00
237 35989
0.530
308
438.16
300.00
233 32932
0.493
306
451.80
300.00
231 31485
0.475
304
458.81
300.00
227 28745
0.442
302
463.54
293.28
223 26201
0.410
299
459.48
280.58
219 23842
0.380
297
455.37
268.17
217 21663
0.348
295
453.12
256.08
217 19677
0.316
295
453.12
244.46
217 17874
0.287
295
453.12
233.34
Low mass CLIMBS
===============
M[-]
0.21
0.21
0.21
0.22
0.22
0.26
0.31
0.42
0.44
0.54
0.56
0.58
0.60
0.63
0.65
0.68
0.70
0.73
0.76
0.78
0.79
0.79
0.79
0.79
0.79
0.79
mass[kg] Thrust[N] Drag[N] Fuel[kgm] ESF[-] ROC[fpm] TDC[N]
104400
297160
85670
215.8
0.98
2452
186284
104400
294268
85680
213.9
0.98
2435
183727
104400
291385
85691
212.0
0.98
2417
181179
104400
288510
82072
211.0
0.97
2527
181833
104400
285643
82082
209.1
0.97
2509
179299
104400
279935
72295
209.0
0.96
2937
182892
104400
274260
67093
210.7
0.95
3470
182476
104400
263011
74643
213.7
0.91
4075
165917
104400
251895
74535
206.0
0.91
3925
156222
104400
240914
91120
207.0
0.87
3905
131941
104400
230066
90785
199.1
0.86
3703
122681
104400
219352
90425
191.3
0.85
3495
113561
104400
208772
90038
183.6
0.84
3281
104583
104400
198326
89622
175.8
0.83
3060
95748
104400
188013
89175
168.1
0.82
2834
87059
104400
177835
88694
160.4
0.81
2601
78516
104400
167790
88179
152.7
0.80
2364
70123
104400
157879
87627
145.0
0.79
2122
61879
104400
148102
87036
137.3
0.78
1875
53788
104400
143263
86725
133.4
0.78
1749
49800
104400
133687
83916
124.9
1.09
2184
43839
104400
124245
79587
115.8
1.09
2205
44658
104400
114936
75881
106.8
1.09
1911
39055
104400
105761
72808
98.1
1.00
1470
32953
104400
96720
70398
89.7
1.00
1174
26322
104400
87813
68640
81.5
1.00
855
19173
PWC[-]
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
0.88
1.00
1.00
1.00
1.00
1.00
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
EUROCONTROL
6.7. PTD FILE FORMAT
In addition to the data provided in the PTF file, more detailed climb and descent performance data
are presented in the PTD file. An example of a PTD file for the Airbus A306 aircraft is shown below
(partial listing):
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The performance values presented in the PTD file are a superset of the climb and descent
performance values presented in the PTF file. They are generated in the same conditions as the
corresponding PTF file: same aircraft, same source OPF and APF files, same speed laws, same
mass levels, same temperature and same flight levels. The purpose of this file is mainly to provide
the user with a greater number of computed parameters, especially intermediate parameters used
to compute the final TAS and ROCD, which may be useful to validate an implementation of the
BADA model.
The files contains performance data consisting of 4 sections:
- low mass climb performance
- nominal mass climb performance
- high mass climb performance
- nominal mass descent performance
Each section contains a table that presents, for several flight levels, a set of performance
parameters spread across 16 columns. Each of these columns is described below:
Column 1
Column 2
Column 3
Column 4
Column 5
Column 6
Column 7
Column 8
Column 9
Column 10
Column 11
Column 12
Column 13
Column 14
Column 15
Column 16
Flight level [FL]
Temperature [K]
Pressure [Pa]
Air density [kg/m3]
Speed of sound [m/s]
TAS [kt]
CAS [kt]
Mach [dimensionless]
Mass [kg]
Thrust [N]
Drag [N]
Fuel flow [kg/min]
Energy share factor [dimensionless]
Rate of climb/descent [ft/min]
(Thr – D) · Cpow,red [kg/min] (see section 3.8)
- climb tables: Power reduction coefficient Cpow,red [dimensionless]
- descent table: Descent gradient [degree]
The format for data presented in each line of the table is as follows (Fortran notation):
Climb tables:
I6, 1X, I3, 1X, I6, 1X, F7.3, 1X, I7, 2(1X, F8.2), 1X, F7.2, 1X, I6, 2(1X, I9), 1X, F7.1, 1X, F7.2, 1X,
I7, 1X, I8, 1X, F7.2
Descent tables:
I6, 1X, I3, 1X, I6, 1X, F7.3, 1X, I7, 2(1X, F8.2), 1X, F7.2, 1X, I6, 2(1X, I9), 1X, F7.1, 1X, F7.2, 1X,
I7, 1X, I8, 1X, F8.2
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6.8. BADA.GPF FILE FORMAT
The BADA.GPF file is an ASCII file which specifies the values of the global aircraft parameters
(see Section 5). The complete BADA.GPF file is shown below:
CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC BADA.GPF CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC/
CC
/
CC
GLOBAL PARAMETERS FILE
/
CC
/
CC
File_name: BADA.GPF
/
CC
/
CC
Creation_date: Mar 26 2002
/
CC
/
CC
Modification_date: Mar 26 2002
/
CC
/
CC
/
CC======== Class ====================================================================/
CC
/
CC Flight = civ,mil
/
CC Engine = jet,turbo,piston
/
CC Phase = to,ic,cl,cr,des,hold,app,lnd,gnd
/
CC
/
CC======== Parameters List ==========================================================/
CC
/
CC Name
Unit
/
CC Parameter
Flight Engine
Phase
Value
/
CC
/
CC max. long. acc. [fps2]
/
CD acc_long_max
civ
jet,turbo,piston to,ic,cl,cr,des,hold,app,lnd .20000E+01 /
CC max. norm. acc. [fps2]
/
CD acc_norm_max
civ
jet,turbo,piston to,ic,cl,cr,des,hold,app,lnd .50000E+01 /
CC nom. bank angle [deg]
/
CD ang_bank_nom
civ
jet,turbo,piston to,lnd
.15000E+02 /
CC nom. bank angle [deg]
/
CD ang_bank_nom
civ
jet,turbo,piston ic,cl,cr,des,hold,app
.35000E+02 /
CC nom. bank angle [deg]
/
CD ang_bank_nom
mil
jet,turbo,piston to,ic,cl,cr,des,hold,app,lnd .50000E+02 /
CC max. bank angle [deg]
/
CD ang_bank_max
civ
jet,turbo,piston to,lnd
.25000E+02 /
CC max. bank angle [deg]
/
CD ang_bank_max
civ
jet,turbo,piston hold
.35000E+02 /
CC max. bank angle [deg]
/
CD ang_bank_max
civ
jet,turbo,piston ic,cl,cr,des,app
.45000E+02 /
CC max. bank angle [deg]
/
CD ang_bank_max
mil
jet,turbo,piston to,ic,cl,cr,des,hold,app,lnd .70000E+02 /
CC exp. desc. fact. [-]
/
CD C_des_exp
civ,mil jet,turbo,piston des
.16000E+01 /
CC to thrust factor [-]
/
CD C_th_to
mil,civ jet,turbo,piston to
.12000E+01 /
CC cr thrust factor [-]
/
CD C_th_cr
mil,civ jet,turbo,piston cr
.95000E+00 /
CC max alt for to [ft]
/
CD H_max_to
mil,civ jet,turbo,piston to
.40000E+03 /
CC max alt for ic [ft]
/
CD H_max_ic
mil,civ jet,turbo,piston ic
.20000E+04 /
CC max alt for app [ft]
/
CD H_max_app
mil,civ jet,turbo,piston app
.80000E+04 /
CC max alt for ld [ft]
/
CD H_max_ld
mil,civ jet,turbo,piston lnd
.30000E+04 /
CC min speed coef. [-]
/
CD C_v_min
mil,civ jet,turbo,piston cr,ic,cl,des,hold,app,lnd
.13000E+01 /
CC min speed coef. [-]
/
CD C_v_min_to
mil,civ jet,turbo,piston to
.12000E+01 /
CC spd incr FL < 15 [KCAS]
/
CD V_cl_1
mil,civ jet
cl
.50000E+01 /
CC spd incr FL < 30 [KCAS]
/
CD V_cl_2
mil,civ jet
cl
.10000E+02 /
CC spd incr FL < 40 [KCAS]
/
CD V_cl_3
mil,civ jet
cl
.30000E+02 /
CC spd incr FL < 50 [KCAS]
/
CD V_cl_4
mil,civ jet
cl
.60000E+02 /
CC spd incr FL < 60 [KCAS]
/
CD V_cl_5
mil,civ jet
cl
.80000E+02 /
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CC spd incr FL < 5 [KCAS]
/
CD V_cl_6
mil,civ turbo,piston
cl
.20000E+02 /
CC spd incr FL < 10 [KCAS]
/
CD V_cl_7
mil,civ turbo,piston
cl
.30000E+02 /
CC spd incr FL < 15 [KCAS]
/
CD V_cl_8
mil,civ turbo,piston
cl
.35000E+02 /
CC spd incr FL < 10 [KCAS]
/
CD V_des_1
mil,civ jet,turbo
des
.50000E+01 /
CC spd incr FL < 15 [KCAS]
/
CD V_des_2
mil,civ jet,turbo
des
.10000E+02 /
CC spd incr FL < 20 [KCAS]
/
CD V_des_3
mil,civ jet,turbo
des
.20000E+02 /
CC spd incr FL < 30 [KCAS]
/
CD V_des_4
mil,civ jet,turbo
des
.50000E+02 /
CC spd incr FL < 5 [KCAS]
/
CD V_des_5
mil,civ piston
des
.50000E+01 /
CC spd incr FL < 10 [KCAS]
/
CD V_des_6
mil,civ piston
des
.10000E+02 /
CC spd incr FL < 15 [KCAS]
/
CD V_des_7
mil,civ piston
des
.20000E+02 /
CC hold. spd FL < 140 [KCAS]
/
CD V_hold_1
mil,civ jet,turbo,piston hold
.23000E+03 /
CC hold. spd FL < 200 [KCAS]
/
CD V_hold_2
mil,civ jet,turbo,piston hold
.24000E+03 /
CC hold. spd FL < 340 [KCAS]
/
CD V_hold_3
mil,civ jet,turbo,piston hold
.26500E+03 /
CC hold. spd FL > 340 [M]
/
CD V_hold_4
mil,civ jet,turbo,piston hold
.83000E+00 /
CC backtrack spd
[KCAS]
/
CD V_backtrack
mil,civ jet,turbo,piston gnd
.35000E+02 /
CC taxi spd
[KCAS]
/
CD V_taxi
mil,civ jet,turbo,piston gnd
.15000E+02 /
CC apron spd
[KCAS]
/
CD V_apron
mil,civ jet,turbo,piston gnd
.10000E+02 /
CC gate spd
[KCAS]
/
CD V_gate
mil,civ jet,turbo,piston gnd
.50000E+01 /
CC Piston pow. red. [-]
/
CD C_red_piston
mil,civ piston
ic,cl
.000000+00 /
CC Turbo pow. red. [-]
/
CD C_red_turbo
mil,civ turbo
ic,cl
.250000+00 /
CC Jet power red.
[-]
/
CD C_red_jet
mil,civ jet
ic,cl
.150000+00 /
FI===================================================================================/
CC////////////////////////////// THE END ///////////////////////////////////////////
There are three types of lines in the BADA.GPF file with the line type identified by the first two
characters in the line. These line types with their associated two leading characters are listed
below.
CC
comment line
CD
data line
FI
end-of-file line
The data is organised into three blocks separated by a comment line consisting of the block name
and equal signs "=":
•
•
•
file identification block
class block
parameter block
Each of these blocks is described in the subsections below.
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6.8.1. File Identification Block
The file identification block provides information on the file name, creation and modification date.
The block consists of 12 comment lines.
CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC BADA.GPF CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC/
CC
/
CC
GLOBAL PARAMETERS FILE
/
CC
/
CC
File_name: BADA.GPF
/
CC
/
CC
Creation_date: Mar 26 2002
/
CC
/
CC
Modification_date: Mar 26 2002
/
The comment lines specify the file name along with the creation date and last modification date.
The creation date indicates the date when the file was created for the first time. The modification
date indicates when the contents of the file were last modified.
6.8.2. Class Block
The class block consists of 6 comment lines and defines the three classes (Flight, Engine and
Phase) and their instances that are used in the BADA.GPF file.
CC======== Class ====================================================================/
CC
/
CC Flight = civ,mil
/
CC Engine = jet,turbo,piston
/
CC Phase = to,ic,cl,cr,des,hold,app,lnd,gnd
/
CC
/
With: civ
mil
jet
turbo
piston
to
ic
cl
cr
des
hold
app
lnd
gnd
=
=
=
=
=
=
=
=
=
=
=
=
=
=
civil flight
military flight
jet engine
turboprop engine
piston engine
take-off
initial climb
climb
cruise
descent
holding
approach
landing
ground
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6.8.3. Parameter Block
The parameter block contains the values of the global aircraft parameters. This block has 5
comment lines plus a comment line and a dataline for each parameter.
1 ->
2 ->
3 ->
CC======== Parameters List
CC
CC Name
Unit
CC Parameter
Flight
CC
CC max. long. acc. [fps2]
CD acc_long_max
civ
CC max. norm. acc. [fps2]
CD acc_norm_max
civ
CC nom. bank angle [deg]
CD ang_bank_nom
civ
==========================================================/
/
/
Engine
Phase
Value
/
/
/
jet,turbo,piston to,ic,cl,cr,des,hold,app,lnd .20000E+01 /
/
jet,turbo,piston to,ic,cl,cr,des,hold,app,lnd .50000E+01 /
/
jet,turbo,piston to,lnd
.15000E+02 /
The parameter comment line contains the parameter name and its unit.
The parameter data line contains five fields:
(a)
Parameter Field:
This field identifies the parameter.
(b)
Flight Field:
This field identifies whether the parameter is valid for a civil flight, a
military flight or both.
(c)
Engine Field:
This field identifies the engine type (jet, turboprop or piston) for
which the parameter is valid.
(d)
Phase Field:
This field identifies for which flight phase the parameter is valid. 8
different flight phases are currently defined
(e)
Value Field:
The value field gives the value of the parameter.
The fields above are specified in the following fixed format (Fortran notation):
'CD', 1X, A15, 1X, A7, 1X, A16, 1X, A29, 1X, E10.5
The parameter list continues until 'FI' (end of file) is reached.
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7. REMOTE FILE ACCESS
The files associated with BADA Revision 3.9 are accessible through the BADA Support Application
(BSA). The BSA is a Web application that provides BADA users with the ability to exchange
requests, as well as data files and documents, with the BADA team members. It is also used for
data repository of the BADA release files and documents.
The right to use the BSA is granted to the licensed user of BADA. The application can be accessed
by using a dedicated login and password as provided by the BADA team.
Once granted the access right to BSA, the user can access the application at this address:
https://remedyweb.eurocontrol.fr
by using the BADA Support Application link and logging in with the provided login/password.
Once logged in, the user can access BADA releases through the Librairies→Releases item located
in the main menu:
Then the release library page opens up, from where the user can download the BADA release
files:
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
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This process, as well as the general usage of the BSA application, is described in detail in [RD11].
Note that enquiries can be addressed to the following addresses:
E-mail:
[email protected]
Fax: + 33 1 69 88 73 33
BADA web page: http://www.eurocontrol.int/eec/public/standard_page/proj_BADA.html
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APPENDIX A
BADA 3.9 – LIST OF AVAILABLE AIRCRAFT MODELS
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Table 7-1: List of Aircraft Types Supported by BADA 3.9
A/C
Code
Model
Type
Aircraft
manufacturer
Aircraft model
Synonym
aircraft
hMO
[ft]
A10
equiv.
FAIRCHILD
THUNDERBOLT II
FGTN
50000
A124
equiv.
ANTONOV
AN-124 RUSLAN
A345
41450
32862
H
A306
direct
AIRBUS
A300B4-600
A306
41000
32378
H
A30B
direct
AIRBUS
A300B4-200
A30B
39000
31967
H
A310
direct
AIRBUS
A310
A310
41000
35719
H
A318
direct
AIRBUS
A318
A318
39800
37606
M
A319
direct
AIRBUS
A319
A319
41000
36365
M
A320
direct
AIRBUS
A320
A320
41000
33965
M
A321
direct
AIRBUS
A321
A321
39100
35396
M
A332
direct
AIRBUS
A330-200
A332
41000
36211
H
A333
direct
AIRBUS
A330-300
A333
41000
36392
H
A342
equiv.
AIRBUS
A340-200
A343
41000
32325
H
A343
direct
AIRBUS
A340-300
A343
41000
32325
H
A345
direct
AIRBUS
A340-500
A345
41450
32862
H
A346
direct
AIRBUS
A340-600
A346
41500
33613
H
A388
direct
AIRBUS
A380-800
A388
43100
34330
J
A3ST
direct
AIRBUS
A-300ST Beluga
A3ST
35000
H
A4
equiv.
DOUGLAS
SUPER SKYHAWK
FGTN
50000
M
A400
equiv.
AIRBUS
A-400M
A3ST
35000
H
A6
equiv.
GRUMMAN
INTRUDER
FGTN
50000
M
A7
equiv.
VOUGHT
CORSAIR II A7
FGTN
50000
M
A748
equiv.
AVRO
AVRO 748
ATP
25000
AA5
equiv.
GULFSTREAM
P28A
12000
L
AC90
equiv.
ROCKWELL
Cheetah AA-5
Turbo Commander
690B
PAY3
33000
L
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hmax
[ft]
WTC
M
21628
M
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72
A/C
Code
Model
Type
Aircraft
manufacturer
Synonym
aircraft
hMO
[ft]
AC95
equiv.
GULFSTREAM
Jetprop
Commander 980
PAY3
33000
L
AEST
equiv.
TED SMITH
AEROSTAR
MU2
28000
L
AJET
equiv.
DASSAULT
ALPHA JET
FGTN
50000
M
AMX
equiv.
EMBRAER
AMX
FGTN
50000
M
AN12
equiv.
ANTONOV
AN-12
C130
32000
21892
M
AN24
equiv.
ANTONOV
AN-124
F27
25000
22778
M
AN26
equiv.
ANTONOV
AN-26
E120
32000
M
AN28
equiv.
ANTONOV
AN-28
D228
28000
L
AN72
equiv.
ANTONOV
AN-72
F28
35000
M
ASTR
equiv.
IAI
1125 Astra
FA10
45000
M
AT43
direct
ATR
ATR 42-300
AT43
25000
22700
M
AT44
equiv.
ATR
ATR 42-400
AT45
25000
23592
M
AT45
direct
ATR
ATR 42-500
AT45
25000
23592
M
AT46
equiv.
ATR
ATR 42-600
AT45
25000
23592
M
AT72
direct
ATR
ATR 72-200
AT72
25000
20317
M
AT73
direct
ATR
ATR 72-210
AT73
25000
20943
M
AT75
direct
ATR
ATR 72-500
AT75
25000
20779
M
AT76
equiv.
ATR
ATR 72-600
AT75
25000
20779
M
ATLA
equiv.
DASSAULT
E120
32000
ATP
direct
BAE
1150 ATLANTIC
ADVANCED
TURBOPROP
ATP
25000
B1
equiv.
ROCKWELL
B1 LANCER
FGTL
41000
H
B190
equiv.
BEECH
JS32
25000
L
B350
equiv.
BEECH
1900
SUPER KING AIR
350
BE20
35000
L
B461
equiv.
BAE
146-100/RJ
B462
31000
30350
M
B462
direct
BAE
146-200/RJ
B462
31000
30350
M
Aircraft model
hmax
[ft]
WTC
M
21628
M
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A/C
Code
Model
Type
Aircraft
manufacturer
Aircraft model
Synonym
aircraft
hMO
[ft]
hmax
[ft]
WTC
B463
equiv.
BAE
146-300/RJ
B462
31000
30350
M
B52
equiv.
BOEING
B-52 Stratofortress
FGTL
41000
B701
equiv.
BOEING
707-100
B752
42000
B703
direct
BOEING
707-300
B703
42000
B712
direct
BOEING
717-200
B712
37000
35188
M
B720
equiv.
BOEING
B720B
B752
42000
35478
M
B721
equiv.
BOEING
727-100
B752
42000
35478
M
B722
direct
BOEING
727-200
B722
37000
33845
M
B731
equiv.
BOEING
737-100
T134
39000
34765
M
B732
direct
BOEING
737-200
B732
37000
34508
M
B733
direct
BOEING
737-300
B733
39000
33637
M
B734
direct
BOEING
737-400
B734
37000
33448
M
B735
direct
BOEING
737-500
B735
37000
34340
M
B736
direct
BOEING
737-600
B736
41000
39276
M
B737
direct
BOEING
737-700
B737
41000
37333
M
B738
direct
BOEING
737-800
B738
41000
34983
M
B739
direct
BOEING
737-900
B739
41000
34683
M
B741
equiv.
BOEING
747-100
B743
45000
30944
H
B742
direct
BOEING
747-200
B742
45000
33180
H
B743
direct
BOEING
747-300
B743
45000
30944
H
B744
direct
BOEING
747-400
B744
45000
32727
H
B748
equiv.
BOEING
B77W
43100
34314
H
B74D
equiv.
BOEING
747-8
747-400
DOMESTIC
B744
45000
32727
H
B74R
equiv.
BOEING
747SR
B743
45000
30944
H
B74S
equiv.
BOEING
747-SP
B742
45000
33180
H
B752
direct
BOEING
757-200
B752
42000
35478
M
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H
35478
M
H
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74
A/C
Code
Model
Type
Aircraft
manufacturer
Aircraft model
Synonym
aircraft
hMO
[ft]
hmax
[ft]
WTC
B753
direct
BOEING
757-300
B753
43000
33340
M
B762
direct
BOEING
767-200
B762
43000
35861
H
B763
direct
BOEING
767-300
B763
43100
36502
H
B764
direct
BOEING
767-400
B764
45000
33210
H
B772
direct
BOEING
777-200 ER
B772
43100
34643
H
B773
direct
BOEING
777-300
B773
43100
31858
H
B77L
direct
BOEING
777-200 LRF
B77L
43100
35104
H
B77W
direct
BOEING
777-300 ER
B77W
43100
34314
H
B788
equiv.
BOEING
787-8
B773
43100
31858
H
BA11
direct
BAE
111 ALL SERIES
BA11
35000
M
BDOG
equiv.
BAE
SA-3 BULLDOG
PA34
25000
L
BE10
equiv.
BEECH
D228
28000
L
BE20
direct
BEECH
BE20
35000
L
BE30
equiv.
BEECH
KING AIR 100
SUPER KING AIR
200
SUPER KING AIR
300
BE20
35000
L
BE33
equiv.
BEECH
BONANZA 33
TRIN
25000
L
BE36
equiv.
BEECH
BONANZA 36
DA42
18000
L
BE40
equiv.
BEECH
BEECHJET 400
C560
45000
BE55
equiv.
BEECH
BARON 55
PA27
20000
L
BE58
direct
BEECH
BARON 58
BE58
25000
L
BE60
equiv.
BEECH
DUKE 60
C421
30000
L
BE76
equiv.
BEECH
DUCHESSE 76
DA42
18000
L
BE95
equiv.
BEECH
TRAVEL AIR 95
TRIN
25000
L
BE99
direct
BEECH
AIRLINER C99
BE99
15000
L
BE9L
direct
BEECH
KING AIR 90
BE9L
31000
L
BE9T
equiv.
BEECH
KING AIR 90
BE9L
31000
L
41083
M
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
A/C
Code
Model
Type
Aircraft
manufacturer
Aircraft model
BN2P
equiv.
equiv.
BRITTENNORMAN
BRITTENNORMAN
BN-2A MARITIME
DEFENDER
BN-2T Defender
4000
BN2T
C130
direct
LOCKHEED
C135
equiv.
BOEING
C141
equiv.
C160
EUROCONTROL
Synonym
aircraft
hMO
[ft]
PA34
25000
L
E120
32000
M
C130
32000
B703
42000
LOCKHEED
HERCULES
STRATOLIFTER C135C
STARLIFTER C141
A310
41000
35719
H
direct
TRANSALL
C160
C160
30000
25500
M
C17
equiv.
BOEING
GLOBEMASTER 3
B764
45000
33210
H
C170
equiv.
CESSNA
170
P28A
12000
L
C172
equiv.
CESSNA
SKYHAWK 172
P28A
12000
L
C177
equiv.
CESSNA
CARDINAL 177
P28A
12000
L
C182
equiv.
CESSNA
SKYLANE 182
TRIN
25000
L
C208
equiv.
CESSNA
CARAVAN
PA27
20000
L
C210
equiv.
CESSNA
CENTURION
TRIN
25000
L
C212
equiv.
CASA
T-12 AVIOCAR
D228
28000
L
C25A
equiv.
CESSNA
525A Citation CJ2
C560
45000
41083
M
C25B
equiv.
CESSNA
525B Citation CJ3
C560
45000
41083
M
C25C
equiv.
CESSNA
525C Citation CJ4
LJ35
45000
40288
M
C27J
equiv.
ALENIA
C-27J Spartan
E120
32000
C295
equiv.
CASA
C-295
ATP
25000
C303
equiv.
CRUSADER 303
PA31
26300
C30J
equiv.
CESSNA
LOCKHEED
MARTIN
C130J HERCULES
C130
32000
C310
equiv.
CESSNA
PA34
25000
L
C337
equiv.
CESSNA
310
SUPER
SKYMASTER
PA27
20000
L
C340
equiv.
CESSNA
C-340/340A
C421
30000
L
C402
equiv.
CESSNA
402
PA34
25000
L
C404
equiv.
CESSNA
TITAN
BE58
25000
L
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
hmax
[ft]
21892
WTC
M
H
M
21628
M
L
21892
M
75
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
76
A/C
Code
Model
Type
Aircraft
manufacturer
Aircraft model
Synonym
aircraft
hMO
[ft]
hmax
[ft]
C414
equiv.
CESSNA
PA31
26300
L
C421
direct
CESSNA
CHANCELLOR 414
GOLDEN EAGLE
421
C421
30000
L
C425
equiv.
CESSNA
CORSAIR
PAY2
29000
L
C441
equiv.
CESSNA
Conquest
PAY3
33000
L
C5
equiv.
LOCKHEED
L-500 GALAXY
A346
41500
C500
equiv.
CESSNA
CITATION 1
C550
43000
L
C501
equiv.
CESSNA
C550
43000
L
C510
direct
CESSNA
CITATION 1SP
CITATION
MUSTANG
C510
41000
L
C525
equiv.
CESSNA
CITATION JET
C550
43000
L
C550
direct
CESSNA
CITATION II-S2
C550
43000
L
C551
equiv.
CESSNA
CITATION 2SP
C550
43000
L
C560
direct
CESSNA
CITATION V
C560
45000
41083
M
C56X
direct
CESSNA
CITATION Excel
C56X
45000
44523
M
C650
equiv.
CESSNA
CITATION VII
LJ35
45000
40288
M
C680
equiv.
CESSNA
Citation Sovereign
F2TH
47000
41486
M
C72R
equiv.
CESSNA
CUTLASS RG
TRIN
25000
C750
direct
CESSNA
CITATION 10
C750
51000
C77R
equiv.
CESSNA
P28A
12000
L
C82R
equiv.
CESSNA
CARDINAL 177RG
SKYLANE R182
RG
TRIN
25000
L
CL30
equiv.
BOMBARDIER
F2TH
47000
41486
M
CL60
direct
CANADAIR
Challenger 300
CHALLENGER
600/601
CL60
41000
39223
M
CN35
equiv.
CASA
CN-235
AT43
25000
22700
M
COL4
equiv.
CESSNA
TRIN
25000
CRJ1
direct
CANADAIR
CRJ1
41000
34334
M
CRJ2
direct
CANADAIR
COLUMBIA 400
REGIONAL JET
CRJ-100
REGIONAL JET
CRJ-200
CRJ2
41000
36856
M
33613
WTC
H
L
45181
M
L
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
A/C
Code
Model
Type
Aircraft
manufacturer
CRJ7
equiv.
CANADAIR
CRJ9
direct
CANADAIR
CVLT
equiv.
D228
Aircraft model
EUROCONTROL
Synonym
aircraft
hMO
[ft]
hmax
[ft]
WTC
CRJ9
41000
36458
M
CRJ9
41000
36458
M
CANADAIR
REGIONAL JET
CRJ-700
REGIONAL JET
CRJ-900
CC-109
COSMOPOLITAN
DH8C
25000
24805
L
direct
DORNIER
228
D228
28000
D328
direct
DORNIER
D328
32800
DA40
equiv.
DIAMOND
328
DA-40-180
DIAMOND STAR
DA42
18000
L
DA42
direct
TWIN STAR
DA42
18000
L
DC10
direct
DIAMOND
MCDONNELL
DOUGLAS
DC-10
DC10
39000
H
DC3
equiv.
DC-3
C421
30000
L
DC85
equiv.
DC-8-50
A310
41000
DC86
equiv.
DC-8-60
DC87
42000
H
DC87
direct
DC-8-70
DC87
42000
H
DC91
equiv.
DC-9-10
B712
37000
DC92
equiv.
DC-9-20
DC94
35000
M
DC93
equiv.
DC-9-30
DC94
35000
M
DC94
direct
DC-9-40
DC94
35000
M
DC95
equiv.
DC-9-50
DC94
35000
M
DH8A
direct
DASH 8-100
DH8A
25000
25000
M
DH8B
equiv.
DASH 8-200
DH8C
25000
24805
L
DH8C
direct
DASH 8-300
DH8C
25000
24805
L
DH8D
direct
DASH 8-400
DH8D
25000
M
DHC6
equiv.
DOUGLAS
MCDONNELL
DOUGLAS
MCDONNELL
DOUGLAS
MCDONNELL
DOUGLAS
MCDONNELL
DOUGLAS
MCDONNELL
DOUGLAS
MCDONNELL
DOUGLAS
MCDONNELL
DOUGLAS
MCDONNELL
DOUGLAS
DE
HAVILLAND
DE
HAVILLAND
DE
HAVILLAND
DE
HAVILLAND
DE
HAVILLAND
CANN.
DHC-6 Twin Otter
D228
28000
L
E110
equiv.
EMBRAER
SW4
25000
E120
direct
EMBRAER
BANDEIRANTE
EMB-120
BRASILIA
E120
32000
M
E121
equiv.
EMBRAER
Xingu
PAY2
29000
L
E135
direct
EMBRAER
EMB-135
E135
41000
M
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
L
29051
35719
35188
25000
M
H
M
L
77
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
78
A/C
Code
Model
Type
Aircraft
manufacturer
Aircraft model
Synonym
aircraft
hMO
[ft]
hmax
[ft]
E145
direct
EMBRAER
EMB-145
E145
37000
M
E170
direct
EMBRAER
EMB-175
E170
41000
M
E190
direct
EMBRAER
EMB-190
E190
41000
M
E3CF
equiv.
BOEING
E-3 SENTRY
B762
43000
35861
H
E3TF
equiv.
BOEING
E-3A SENTRY
B762
43000
35861
H
E50P
direct
EMBRAER
Phenom 100
E50P
41000
40400
L
E55P
direct
EMBRAER
Phenom 300
E55P
45000
44923
M
EA50
direct
ECLIPSE
ECLIPSE 500
EA50
41000
L
ETAR
equiv.
ETENDARD 4
FGTN
50000
M
EUFI
equiv.
DASSAULT
EUROFIGHTE
R
2000
FGTN
50000
M
F1
equiv.
MITSUBISHI
F1
FGTN
50000
M
F100
direct
FOKKER
100
F100
35000
F104
equiv.
LOCKHEED
STARFIGHTER
FGTN
50000
M
F117
equiv.
LOCKHEED
NIGHTHAWK
FGTN
50000
M
F14
equiv.
TOMCAT
FGTN
50000
M
F15
equiv.
50000
M
equiv.
EAGLE
FIGHTING
FALCON
FGTN
F16
FGTN
50000
M
F18
equiv.
GRUMMAN
MCDONNELL
DOUGLAS
GENERAL
DYNAMICS
MCDONNELL
DOUGLAS
HORNET
FGTN
50000
M
F27
direct
FOKKER
FRIENDSHIP
F27
25000
F28
direct
FOKKER
FOLLOWSHIP
F28
35000
F2TH
direct
FALCON 2000
F2TH
47000
F4
equiv.
DASSAULT
MCDONNELL
DOUGLAS
PHANTOM
FGTN
50000
M
F406
equiv.
CESSNA
F406 Vigilant
PAY3
33000
L
F5
equiv.
NORTHROP
F-5
FGTN
50000
M
F50
direct
FOKKER
50
F50
25000
35000
22778
WTC
M
M
M
41486
21331
M
M
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
A/C
Code
Model
Type
Aircraft
manufacturer
Aircraft model
Synonym
aircraft
hMO
[ft]
hmax
[ft]
WTC
F70
direct
FOKKER
70
F70
37000
36565
M
F900
direct
DASSAULT
FALCON 900
F900
51000
38187
M
FA10
direct
DASSAULT
FALCON 10
FA10
45000
M
FA20
direct
DASSAULT
FALCON 20
FA20
42000
M
FA50
direct
DASSAULT
FALCON 50
FA50
49000
41177
M
FA7X
direct
DASSAULT
FA7X
51000
39848
M
FGTH
direct
GENERIC
FGTH
50000
M
FGTL
direct
GENERIC
FGTL
41000
H
FGTN
direct
GENERIC
FALCON 7X
MIL FIGHTER
HEAVY
MIL FIGHTER
LIGHT
MIL FIGHTER
NORMAL
FGTN
50000
M
G120
equiv.
GROB
G-120A
PA27
20000
L
G150
equiv.
IAI
Gulfstream G150
F2TH
47000
41486
M
G222
equiv.
ALENIA
SPARTAN C-27A
ATP
25000
21628
M
G250
equiv.
GULFSTREAM
G250
F2TH
47000
41486
M
GALX
equiv.
IAI
1126 GALAXY
F2TH
47000
41486
M
GL5T
equiv.
Global 5000
C750
51000
45181
M
GLAS
equiv.
BOMBARDIER
STODDARDHAMILTON
BE58
25000
GLEX
equiv.
BOMBARDIER
GLASAIR
BD-700 Global
Express
C750
51000
45181
M
GLF2
equiv.
GULFSTREAM
GULFSTREAM II
FA7X
51000
39848
M
GLF3
equiv.
GULFSTREAM
GULFSTREAM III
FA7X
51000
39848
M
GLF4
equiv.
GULFSTREAM
FA7X
51000
39848
M
GLF5
equiv.
GULFSTREAM
GULFSTREAM IV
GULFSTREAM V
C37
FA7X
51000
39848
M
GLF6
equiv.
GULFSTREAM
G650
FA7X
51000
39848
M
GLST
equiv.
GlaStar
TRIN
25000
L
H25A
direct
DOMINE HS 125
H25A
40000
M
H25B
equiv.
GLASAIR
HAWKER
SIDDELEY
HAWKER
SIDDELEY
HS 125-700/800
H25A
40000
M
H25C
equiv.
RAYTHEON
HAWKER 1000
FA20
42000
M
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
L
79
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
80
A/C
Code
Model
Type
Aircraft
manufacturer
Aircraft model
Synonym
aircraft
hMO
[ft]
HAR
equiv.
HAWK
equiv.
HAWKER
SIDDELEY
HAWKER
SIDDELEY
HELI
equiv.
IL18
hmax
[ft]
HARRIER
FGTN
50000
M
HAWK
FGTN
50000
M
GENERIC
HELICOPTER
P28A
12000
L
equiv.
ILYUSHIN
IL-18
C130
32000
21892
M
IL62
equiv.
ILYUSHIN
IL-62 /-62M / MK
A30B
39000
31967
H
IL76
equiv.
ILYUSHIN
IL-76
B764
45000
33210
H
IL86
equiv.
ILYUSHIN
IL-86
B763
43100
36502
H
IL96
equiv.
IL-96
A343
41000
32325
H
J328
equiv.
ILYUSHIN
FAIRCHILD
DORNIER
328 Jet
E135
41000
M
JAGR
equiv.
SEPECAT
JAGUAR
FGTN
50000
M
JS1
equiv.
JETSTREAM
JETSTREAM 1
BE20
35000
L
JS20
equiv.
JETSTREAM
JETSTREAM 200
D228
28000
L
JS31
equiv.
BAE
JS32
25000
L
JS32
direct
JETSTREAM
JETSTREAM 31
JETSTREAM Super
31
JS32
25000
L
JS41
direct
JETSTREAM
JS41
26000
K35A
equiv.
BOEING
B703
42000
H
K35E
equiv.
BOEING
B703
42000
H
K35R
equiv.
BOEING
JETSTREAM 41
STRATOTANKER
KC-135A
STRATOTANKER
KC-135D/E
STRATOTANKER
K35R
B703
42000
H
L101
direct
LOCKHEED
TRISTAR L-1011
L101
42000
H
L159
equiv.
AERO (2)
L-159
FGTN
50000
M
L188
equiv.
LOCKHEED
ELECTRA L-188
C160
30000
25500
M
L29A
equiv.
LOCKHEED
JETSTART
CL60
41000
39223
M
L29B
equiv.
LOCKHEED
L1329 JETSTAR
CL60
41000
39223
M
L410
equiv.
LET
TURBOLET 410
D228
28000
LJ24
equiv.
LEARJET
24
C560
45000
24685
WTC
M
L
41083
M
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
A/C
Code
Model
Type
Aircraft
manufacturer
Aircraft model
Synonym
aircraft
hMO
[ft]
hmax
[ft]
WTC
LJ25
equiv.
LEARJET
25
LJ45
51000
44100
M
LJ31
equiv.
LEARJET
31
LJ45
51000
44100
M
LJ35
direct
LEARJET
35
LJ35
45000
40288
M
LJ40
equiv.
LEARJET
40
LJ45
51000
44100
M
LJ45
direct
LEARJET
45
LJ45
51000
44100
M
LJ55
equiv.
LEARJET
55
LJ45
51000
44100
M
LJ60
equiv.
LEARJET
60
LJ45
51000
44100
M
M20P
equiv.
MOONEY
MARK 201
TRIN
25000
L
M20T
equiv.
MARK 20T
TRIN
25000
L
MD11
direct
MD-11
MD11
43000
31838
H
MD81
equiv.
MD-81
MD82
37000
34448
M
MD82
direct
MD-82
MD82
37000
34448
M
MD83
direct
MD-83
MD83
37000
33513
M
MD87
equiv.
MD-87
MD82
37000
34448
M
MD88
equiv.
MD-88
MD82
37000
34448
M
MD90
equiv.
MOONEY
MCDONNELL
DOUGLAS
MCDONNELL
DOUGLAS
MCDONNELL
DOUGLAS
MCDONNELL
DOUGLAS
MCDONNELL
DOUGLAS
MCDONNELL
DOUGLAS
MCDONNELL
DOUGLAS
MD-90
MD83
37000
33513
M
MG21
equiv.
MIKOYAN
MIG-21
FGTN
50000
M
MG23
equiv.
MIKOYAN
MIG-23
FGTN
50000
M
MG25
equiv.
MIKOYAN
MIG-25
FGTN
50000
M
MG29
equiv.
MIKOYAN
MIG-29
FGTN
50000
M
MIR2
equiv.
DASSAULT
MIRAGE 2000
FGTN
50000
M
MIR4
equiv.
DASSAULT
MIRAGE IV
FGTN
50000
M
MRF1
equiv.
DASSAULT
FGTN
50000
M
MU2
direct
MITSUBISHI
MIRAGE F1
MARQUISE/SOLIT
AIRE
MU2
28000
L
MU30
equiv.
MITSUBISHI
MU-300
C560
45000
41083
M
N262
equiv.
NORD
262
JS41
26000
24685
M
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
81
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
82
A/C
Code
Model
Type
Aircraft
manufacturer
Aircraft model
Synonym
aircraft
hMO
[ft]
hmax
[ft]
WTC
NIM
equiv.
HAWKER
SIDDELEY
NIMROD
B738
41000
34983
M
P180
equiv.
PIAGGIO
P180 AVANTI
PA-28-140
CHEROKEE
PA-28-236
DAKOTA
PA-28R-201
ARROW
PA-28RT TURBO
ARROW 4
C550
43000
L
P28A
direct
PIPER
P28A
12000
L
P28B
equiv.
PIPER
TRIN
25000
L
P28R
equiv.
PIPER
DA42
18000
L
P28T
equiv.
PIPER
DA42
18000
L
P3
equiv.
LOCKHEED
C130
32000
PIPER
ORION P-3
PA-32R-301
SARATOGA SP
P32R
equiv.
TRIN
25000
L
P46T
equiv.
PIPER
Malibu Meridian
BE9L
31000
L
P68
equiv.
PARTENAVIA
P-68 Observer
PA27
20000
L
PA18
equiv.
PIPER
PA34
25000
L
PA23
equiv.
PIPER
PA27
20000
L
PA27
direct
PIPER
PA-18 SUPER CUB
APACHE PA23150/160
AZTEC PA23235/250
PA27
20000
L
PA30
equiv.
PIPER
Twin Comanche
TRIN
25000
L
PA31
direct
PIPER
PA31
26300
L
PA32
equiv.
PIPER
TRIN
25000
L
PA34
direct
PIPER
CHIEFTAIN
PA-32 CHEROKEE
SIX
PA34-200T
SENECA-III
PA34
25000
L
PA44
equiv.
PIPER
PA-44 SEMINOLE
TRIN
25000
L
PA46
equiv.
PIPER
BE58
25000
L
PAY1
equiv.
PIPER
PAY2
29000
L
PAY2
direct
PIPER
PAY2
29000
L
PAY3
direct
PIPER
PAY3
33000
L
PAY4
equiv.
PIPER
Malibu
PA-A-31T1-500
CHEYENNE I
PA-31T-620
CHEYENNE II
PA-42-720
CHEYENNE III
PA-42-1000
CHEYENNE 400
C510
41000
L
PC12
equiv.
PC-12 SPECTRE
BE9L
31000
L
PRM1
equiv.
PILATUS
HAWKER
BEECHCRAFT
390 Premier 1
C560
45000
21892
41083
M
M
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
A/C
Code
Model
Type
Aircraft
manufacturer
Aircraft model
Synonym
aircraft
hMO
[ft]
RFAL
equiv.
DASSAULT
RAFALE
FGTN
50000
RJ1H
equiv.
AI(R)
RJ-100 Avroliner
RJ85
35000
31355
M
RJ70
equiv.
AI(R)
RJ-70 Avroliner
RJ85
35000
31355
M
RJ85
direct
AI(R)
RJ85
35000
31355
M
S601
equiv.
AEROSPATIAL
RJ-85 Avroliner
SB 601
CORVETTE
C550
43000
L
SB05
equiv.
SAAB
SAAB 105
C510
41000
L
SB20
direct
SAAB
SAAB 2000
SB20
31000
M
SB32
equiv.
SAAB
LANSEN
FGTN
50000
M
SB35
equiv.
SAAB
DRAKEN
FGTN
50000
M
SB37
equiv.
SAAB
VIGGEN
FGTN
50000
M
SB39
equiv.
SAAB
GRIPEN
FGTN
50000
M
SBR1
equiv.
ROCKWELL
SABRELINER
FA10
45000
M
SF34
direct
SAAB
SF 340
SF34
25000
SH33
equiv.
SHORTS
SH3-330
SH36
20000
M
SH36
direct
SHORTS
SH3-360
SH36
20000
M
SR20
equiv.
CIRRUS
SR-20
DA42
18000
L
SR22
equiv.
CIRRUS
SR-22
TRIN
25000
L
SW2
equiv.
SWEARINGEN
MERLIN II
SW4
25000
SW3
equiv.
SWEARINGEN
MERLIN III
PAY3
33000
SW4
direct
SWEARINGEN
MERLIN IV
SW4
25000
25000
L
T134
direct
TUPOLEV
TU134A-3
T134
39000
34765
M
T154
direct
TUPOLEV
TU154M
T154
41000
37285
M
T160
equiv.
TUPOLEV
TU160
B742
45000
33180
H
T204
equiv.
TUPOLEV
TU 204
T154
41000
37285
M
TBM7
direct
SOCATA
TBM-700
TBM7
31000
L
TBM8
equiv.
SOCATA
TBM-850
TBM7
31000
L
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
hmax
[ft]
WTC
M
24369
25000
M
L
L
83
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
84
A/C
Code
Model
Type
Aircraft
manufacturer
Aircraft model
Synonym
aircraft
hMO
[ft]
hmax
[ft]
TOBA
equiv.
SOCATA
TOBAGO TB-10
TRIN
25000
L
TOR
equiv.
PANAVIA
TORNADO
FGTN
50000
M
TRIN
direct
TRINIDAD TB-20
TRIN
25000
L
TRIS
equiv.
SOCATA
BRITTENNORMAN
Trislander
DA42
18000
L
VC10
equiv.
VICKERS
VC10
B762
43000
WW24
equiv.
IAI
1124 WESTWIND
FA10
45000
M
YK40
equiv.
YAKOLEV
YAK-40
E120
32000
M
YK42
equiv.
YAKOLEV
YAK-42
DC94
35000
M
35861
WTC
H
Project BADA – EEC Technical/Scientific Report No. 11/03/08-08
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
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85
EUROCONTROL
User Manual for the Base of Aircraft Data (BADA) Revision 3.9
APPENDIX B
SOLUTIONS FOR BUFFETING LIMIT ALGORITHM
86
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User Manual for the Base of Aircraft Data (BADA) Revision 3.9
EUROCONTROL
A general solution for finding the roots of a cubic expression can be found in [RD15]. If we take
expression 3.6-6, we can rewrite it to:
Μ3 −
C Lbo ( M =0 )
k
W
S
⋅ Μ2 +
=0
0.583 ⋅ P ⋅ k
Therefore:
a1 = −
C Lbo ( M =0 )
k
a2 = 0
W
S
a3 =
0.583 ⋅ P ⋅ k
Now let:
Q=
(3 ⋅ a
R=
(9 ⋅ a
and:
)
2
− a1
9
1
⋅ a 2 − 27 ⋅ a 3 − 2 ⋅ a1 3
54
2
)
The discriminant D is equal to: Q3 + R2 . In our case D is always < 0 which means that all roots are
unequal and real. A simplified computation method with the help of trigonometry is given below:
θ a
Χ1 = 2 ⋅ − Q ⋅ cos − 1
3 3
θ
a
Χ 2 = 2 ⋅ − Q ⋅ cos + 120 0 − 1
3
3
θ
a
Χ 3 = 2 ⋅ − Q ⋅ cos + 240 0 − 1
3
3
With: cos θ =
R
− Q3
The solutions X1, X2 and X3 now give the possible values of M. One solution (in our case usually
X1) is always negative. The others are positive with the lower one (usually X2) being the low speed
buffeting limit we are looking for.
88
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89
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