User Manual - Federal Aviation Administration

descent speeds. The User Manual for BADA Revision 3.3 (EUROCONTROL Experimental Centre, 2000) provides definitions of each of the coefficients and then explains the file formats. This manual, along with instructions for remotely accessing the files via Internet, is available through the following site: http://www.eurocontrol.fr/projects/bada/. The BADA Processor module of the Aircraft Modeling Tool uses aircraft designators and performance information from http://www.aopa.org in assessing some of the aircraft flight performance data. A sample BADA file is given in Appendix B. As mentioned above, BADA 3.3 provides operations and procedures data for a total of 186 aircraft types. For 71 of these aircraft types, data are provided directly in files. These aircraft are referred to as being directly supported. For the other 115 aircraft types, the data are specified to be the same as one of the directly supported 71 aircraft types. The second set of aircraft types is referred to as being supported through equivalence. With one exception, each supported aircraft type is identified by a 4-character designation code assigned by the International Civil Aviation Organization (ICAO). The exception is the model representing a generic military fighter, which uses the designator FGTR. The list of aircraft types supported by BADA 3.3 is given in Appendix C. 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 direct or equivalence) is specified. Also, for each aircraft, which is supported through equivalence, the corresponding equivalent aircraft type is specified. A separate document, Equivalences Report for BADA (EUROCONTROL Experimental Centre, 1996), describes the procedure for identifying equivalent aircraft types and investigating the percentage of European traffic covered by aircraft types represented in BADA. This document shows that 71 aircraft types within BADA 3.3 cover about 90% of European air traffic. Separate analysis of National Airspace (NAS) traffic shows that BADA 3.3 covers about 80% of domestic air traffic. The following table shows all jet aircraft represented in BADA 3.3. 3 Table 2.1.1-1 BADA Jet Aircraft Models ## Aircraft Code (BADA) Name or Model Equivalences 1 A306 Airbus A300-B4-622 A30B IL76 2 A30B Airbus A300-B4-203 A306 3 A310 Airbus A310-203 A310 4 A319 Airbus A319-131 A319 5 A320 Airbus A320-111 A320 6 A321 Airbus A321-111 A321 7 A330 Airbus A330 A330 8 A340 Airbus A340-300 A340 9 B703 Boeing B707-300 B703 C135 E3CF B701 IL62 VC10 B720 E3TF 10 B722 Boeing B727-228 B722 B721 11 B732 Boeing B737-228 B732 B731 12 B733 Boeing B737-300QC/B737-300 B733 B734 B735 13 B738 Boeing B737-800 B738 B736 B737 14 B742 Boeing B747-228 B742 B741 B743 C5 15 B744 Boeing B747-400 B744 B74S 16 B752 Boeing B757-200 B752 B753 17 B763 Boeing B767-300ER B763 B762 B764 18 B772 Boeing B772-200 B772 B773 19 BA11 BAC 1.11/400 BA11 20 BA46 BAE146 BA46 YK42 21 C550 Cessna Citation II-CE 550 C550 C551 C500 C525 MU30 S601 SK60 22 C560 Cessna Citation V C560 23 CL60 Canadair Challenger CL600/601 CL60 L29A GLF2 GLF3 GLF4 24 CRJ1 Canadair Regional Jet CRJ1 CRJ2 E145 25 DC10 DC10-30 DC10 26 DC87 DC8-72CF DC87 DC85 DC87 IL86 C141 27 DC9 DC9-40 DC9 28 F100 FOKKER 100 F100 29 F28 Fokker F28 F28 30 F70 FOKKER 70 F70 31 F900 Dassault 900-100 F900 32 FA10 DASSAULT FALCON 10 FA10 33 FA20 DASSAULT FALCON 20 FA20 SBR1 34 FA50 Dassault DA50 FA50 35 FGTR Generic Fighter FGTR TOR F16 JAGR HAR HAWK F4 F15 F18 MG21 MG23 MG25 MG29 CONC MRF1 MIR2 MIR4 A10 A6 F14 SB32 SB35 SB37 SB39 36 H25B BAe 125 Dominie H25B WW24 37 L101 Lockheed L-1011 L101 4 ## Aircraft Code (BADA) Name or Model Equivalences 38 LJ35 Learjet 35A LJ35 C650 LJ31 LJ55 39 MD11 McDonnell-Douglas MD-11 MD11 40 MD80 Douglas MD83 MD80 MD90 41 T134 Tupolev TU 134A-3 T134 42 T154 Tupolev TU-154M T154 The entire list of BADA aircraft along with equivalent aircraft types mapped using various sources of information is listed in Appendix C. 2.1.2 BADA Aircraft Performance Data Aircraft performance data are contained in the Operations Performance Files (.OPF) of BADA. The .OPF file is in ASCII format and a sample of this file for the Boeing 747- 400 (aircraft designator B744) is listed in Appendix B of this report with detailed description of parameters listed in Appendix A. The data are organized into a total of eight blocks listed below and described in further detail in subsections below. • File identification block • Aircraft type block • Mass block • Flight envelope block • Aerodynamics block • Engine thrust block • Fuel consumption block • Ground movements block 2.1.2.1 File Identification Block The file identification block provides information on the file name, revision number and identification date. The last modification revision number and date indicate when the contents of the file were last modified. 2.1.2.2 Aircraft Type Block This block specifies the following aircraft type parameters: • ICAO aircraft code • Number of engines, eng n • Engine type • Wake category 5 The engine type can be one of the following three values: Jet, Turboprop or Piston. The wake category can be one of the three values: H (heavy), M (medium) or L (light). 2.1.2.3 Mass Block This block specifies the following BADA mass model parameters (in tones): • Reference mass, ref m • Minimum mass, min m • Maximum mass, mass m • Payload mass, pyld m • Mass gradient, w G 2.1.2.4 Flight Envelope Block The .OPF flight envelope block specifies the following BADA altitude-speed envelope parameters: • Maximum operating speed, CAS (knots), MO V • Maximum operating Mach number, MO M • Maximum operating altitude (feet), MO h • Temperature gradient, t G 2.1.2.5 Aerodynamics Block This block specifies the following BADA aerodynamic model parameters: • Wing (reference) area (sq. m), S • Compressibility drag coefficient, M16 C • Stall speed for five flight configurations (knots), stall V • Parasite drag coefficient for five flight configurations, D0 C • Induced drag coefficient for five flight configurations, D2 C The five flight configurations modeled in BADA are: 1. CR – cruise 2. IC – initial climb 3. TO – take-off 6 4. AP – approach 5. LD – landing 2.1.2.6 Engine Thrust Block The .OPF engine thrust block specifies the following BADA parameters: • BADA engine coefficients used to calculate the maximum climb thrust, Tc,5 Tc,4 Tc,3 Tc,2 Tc,1 C , C , C , C , C • BADA parameters used to calculate cruise and descent thrust, ld Tdes, app Tdes, des high Tdes, low Tdes, C , C , h , C , C 2.1.2.7 Fuel Consumption Block This block specifies the following BADA fuel consumption model parameters: • BADA parameters for thrust specific fuel consumption, f2 f1 C and C • BADA parameters for descent fuel flow, f4 f3 C and C • The cruise fuel flow correction factor, fcr C 2.1.2.8 Ground Movement Block The .OPF ground movement block is the last block in the .OPF file and specifies BADA parameters for the ground movements not used in TGF. 2.1.3 Installing and Running The following steps outline BADA Processor installation and running procedures: 1. Unzip file TGFwork.zip and save all unzipped files into the same directory (for example TGFwork) 2. Start Matlab 3. In Matlab go to File Menu and select Set Path 4. In Set Path Menu click on Add with Subfolders button and browse to find TGFwork directory 5. Select TGFwork directory and click OK button 6. Click Save button in Set Path Menu Steps 1-6 are implemented only once, i.e. the first time you install the software 7 7. Download BADA data in ZIP format from corresponding Eurocontrol’s ftp site accessed from http://www.eurocontrol.fr/projects/bada/. 8. Unzip this data and save it in BADA folder within TGFwork directory in a single folder badaX.X, where X.X is the version of the data (for example 3.3) Steps 7-8 are implemented each time the new version of BADA aircraft data are available from Eurocontrol (usually once a year) 9. In Matlab command prompt type AircraftFileGenerator. Type the full path of the working directory, i.e. of TGFwork. To find out the full path of the working directory right click on its folder and select Properties, directory’s full path will be listed under Location. Do not forget to add the name of the working directory with slash to its path (Matlab command prompt will have an example). 10. Press enter and type aircraft type to process BADA for – all, jet, turboprop, or piston (lower case, case sensitive) 11. Press enter and enter input directory within working directory that contains BADA data, for example BADA\bada3.3. 12. Press enter and type output directory name within working directory, for example ALL, JET, PROP, or PISTON. 13. Press enter and choose to update or not to update comments to the new file (Y/N). 14. Press enter and if Y is selected in 13 type the comment and the author name. 15. Press enter. The program will run on Pentium III – 750 MHz for about 30 seconds to generate chosen files in selected folder. Once program is running, the following run time screen is displayed. Upon completion of the program the new screen (shown below) will appear 8 Steps 9-15 are implemented each time one needs to run parser. Newly created output directory will contain aircraft_baseline.xml file with all corresponding aircraft models for use in TGF simulator. 2.2 Manual Aircraft Generator 2.2.1 Overview Not all aircraft types are represented in BADA, directly or through equivalence types; therefore, there is a need for a fully manual method in generating necessary input files for TGF. As mentioned before, the theoretical background behind the derivation of the aircraft parameters representing aircraft models in TGF is beyond the scope of this document. It is necessary though for the user to estimate the value of the aircraft parameters shown in Table 2.2-1 to create an input file for generating the required aircraft model. Table 2.2-1 also lists units of the corresponding parameters and sources to obtain these parameters. Table 2.2.1-1 Input Parameters Variable Parameter Units Alternative Calculation Example Aircraft Type AcType Aircraft Type - - B744 EngType Engine Type - - jet Flight Envelope h Cruise altitude (economical for long range), cruise H ft Last reservation - use 35,000 ft 35000 hmax Operating ceiling, max H ft Last reservation - use 41,000 ft 45000 9 Variable Parameter Units Alternative Calculation Example M Cruise Mach number (economical for long range), cruise M - Literature usually gives economical cruising speed in knots rather than Mach number. In this case use function StandardAtmosphere.m to obtain corresponding Mach number for input file (See (*)) 0.85 Weights Wmax Maximum take- off weight, max W lbs - 372*1000/.454 Wnom Nominal weight, nom W lbs From statistical observations max nom W 8 . 0 W ⋅ = 300*1000/.454 Wmin Operating empty weight, min W lbs - 180*1000/.454 Wload Maximum payload weight, load W lbs From statistical observations max nom W 2 . 0 W ⋅ = 61.64*1000/.454 Wing Geometry Sref Reference area, ref S sq. ft Calculate by breaking plan form view, if necessary, into several trapezoids 525*10.7626 AR Aspect ratio, A - Calculate using (2.2.1-2) 7.39 lambda Taper ratio,
- Calculate using (2.2.1-1) 0.275 SWEEPq ¼ Chord sweep, C/4 Λ deg Calculate using (2.2.1-3) 37.5 t_c Thickness ratio, c t/ - From statistical observations 0.1 c t/ ≈ 9.40/100 h_wlt Winglet height, winglet h ft From aircraft front view, use 0 if there are no winglets 0 Fuselage Geometry Df Fuselage diameter, fuselage D ft Measured from aircraft plan form view (Figure 2.2.1-2) 8.10*3.2808 Lf Fuselage length, fuselage L ft Measured from aircraft plan form view (Figure 2.2.1-2) 68.63*3.2808 Lnf Nose section length, nose L ft Measured from aircraft plan form view (Figure 2.2.1-2) 0.2*Lf Ltf Tail section length, tail L ft Measured from aircraft plan form view (Figure 2.2.1-2) 0.3*Lf Horizontal Tail Geometry S_ht Reference area, HT S sq. ft Calculate by breaking plan form view, if necessary, into several trapezoids 136.6*10.7626 AR_ht Aspect ratio, A - Calculate using (2.2.1-2) 3.57 lambda_ht Taper ratio,
- Calculate using (2.2.1-1) 0.265 SWEEPq_ht ¼ Chord sweep, C/4 Λ deg Calculate using (2.2.1-3) 32 t_c_ht Thickness ratio, c t/ - Use the same value as for the wing t_c 10 Variable Parameter Units Alternative Calculation Example Vertical Tail Geometry S_vt Reference area, VT S sq. ft Calculate by breaking plan form view, if necessary, into several trapezoids 77.10*10.7626 AR_vt Aspect ratio, A - Calculate using (2.2.1-2), b in this case is the horizontal tail height 1.34 lambda_vt Taper ratio,
- Calculate using (2.2.1-1) 0.33 SWEEPq_vt ¼ Chord sweep, C/4 Λ deg Calculate using (2.2.1-3) 45 t_c_vt Thickness ratio, c t/ - Use the same value as for the wing t_c Engine Data n_eng Number of engines - - 4 Dn Nacelle diameter, nacelle D ft From aircraft front view 2.9*3.2808 Ln Nacelle length, nacelle L ft From aircraft side view 5.64*3.2808 MaxThrust Maximum static thrust per engine, max T lbs - 57900 For definition of parameters in (2.2.1-1)-(2.2.1-3) refer to Figure 2.2.1-1. root tip C C
= (2.2.1-1) ref 2 S b A = (2.2.1-2) ( ) ( ) A
1
1 tan tan LE C/4 ⋅ + − − = (2.2.1-3) *Determining cruise Mach number given cruise speed in knots using Matlab
: >> [rho,pres_o,pres,Temp,astar,visc,kvisc] = StandardAtmosphere(h) % [rho,pres_o,pres,Temp,astar,visc,kvisc] = StandardAtmosphere(h) % % Determines atmospheric conditions for a given altitude % % Input: % h ........Altitude (ft) % Output: % rho ........ Air density (slugs/ft^3) % pres_o ...... Sea level Pressure (psf) % pres ........ Ambient pressure (psf) % Temp ........ Ambient temperature (R) % astar ....... Speed of Sound (ft/sec) % visc ....... Viscosity (slugs/ft/sec) 11 % kvisc ....... Kinematic Viscosity (ft^2/sec) Note that h is long-range cruise altitude in feet. If cruise speed V is given in knots than cruise Mach number is calculated in Matlab
by using the following formula: >> M = V*1.15*5280/3600/astar 12 Figure 2.2.1-1 Aircraft Geometry (1)1 1 Courtesy of Raymer, D. (1999), Aircraft Design: A Conceptual Approach (Third Edition). American Institute of Aeronautics and Astronautics, Inc., Reston, VA. 13 fuselage L b HT b nose L tail L VT b fuselage D winglet h Figure 2.2.1-2 Aircraft Geometry (2) 14 2.2.2 Manual Aircraft Generator Functions and their Description The following section of this report outlines all major functions of Manual Aircraft Generator Tool. It should be noted that this tool allows for generating only jet aircraft models. Further adjustments need to be made to make this tool suitable for modeling turboprop and piston engine aircraft performance parameters. Table 2.2.2-1 Manual Aircraft Generator Functions Function Purpose Input Output ACFTparam Aircraft input file that contains all the necessary parameters to generate XML file See Table 1 See Input AircraftModel Main program that runs Aircraft Modeling Tool. To run tool, type AircraftModel in Matlab command prompt - - AircraftParameters Main program that calls all the functions to calculate aircraft parameters from the data from ACFTparam ACFTparam data - DragCalculator Main program that calculates aircraft parasite, induced, and compressibility drag coefficients ACFTparam data Cdp – Parasite drag coefficient Cdi – Induced drag coefficient Cdc – Compressibility drag coefficient Cm16 – Compressibility drag coefficient (for BADA drag polar representation) StandardAtmosphere This function calculates standard atmosphere parameters h – Altitude (ft) rho - Air density (slugs/ft^3) pres_o - Sea level Pressure (psf) pres - Ambient pressure (psf) Temp - Ambient temperature (R) astar - Speed of Sound (ft/sec) visc -Viscosity (slugs/ft/sec) kvisc - Kinematic Viscosity (ft^2/sec) 15 Function Purpose Input Output WingGeometry This function calculates some wing, horizontal and vertical tail geometry parameters Sref - Reference area (ft^2) AR - Aspect ratio, i.e. b^2/Sref lambda - Taper ratio, i.e. Ct/Cr SWEEPq - Sweep along quarter chord line (deg) Df - Diameter of the fuselage (ft) b - Span (ft) Cr - Root chord (ft) Ct - Tip chord (ft) SWEEPle - Sweep along leading edge (deg) MAC - Mean aerodynamic chord Swet - Wetted area (ft^2) EffectiveAspectRatio This function calculates effective aspect ratio of the wing with winglets AR - Geometric Aspect Ratio h_wlt - Height of winglet (ft) b - wing span (ft) ARe - Effective Aspect Ratio WingFormFactor This function calculates form factor for the wing, horizontal and vertical tail M - Mach number SWEEPq - Sweep along quarter chord line (deg) t_c - Thickness ratio K – Form factor ReynoldsNumber This function calculates Reynolds number kvisc - Kinematic viscosity (ft^2/sec) TAS - True airspeed (ft/sec) L - Body length (ft) RN - Reynolds number SkinFrictionCoefficient This function calculates skin friction coefficient RN - Reynolds number M - Mach number Cf - Skin friction coefficient FuselageGeometry This function calculates some fuselage and nacelle geometry parameters D - Diameter (ft) L - Length (ft) Lnose - Length of the nose section (ft) Ltail - Length of the tail section (ft) Swet - Wetted area (ft^2) FuselageFormFactor This function calculates fuselage form factor f - Fineness ratio, i.e. L/D Kf - Form factor NacelleFormFactor This function calculates nacelle form factor f - Fineness ratio, i.e. L/D Kn - Form factor OswaldEfficiency This function calculates Oswald efficiency factor SWEEPle - Sweep along leading edge (deg) AR - Aspect ratio e - Oswald Efficiency 16 Function Purpose Input Output CompressibilityDrag This function calculates compressibility drag Cdp – Parasite drag coefficient Cdi – Induced drag coefficient t_c - Thickness ratio SWEEPq - Sweep along quarter chord line (deg) Sref - Reference area (ft^2) M - Mach number Wnom – Nominal weight (lbs) h – Altitude (ft) Cdc – Compressibility drag coefficient Cm16 – Compressibility drag coefficient (for BADA drag polar representation) DragCoefficients This function calculates parasite and induced drag coefficient for 5 flight configurations Cdp – Parasite drag coefficient Cdi – Induced drag coefficient Cd1_lift, Cd2_lift, Cd3_lift, Cd4_lift, Cd5_lift – Parasite drag coefficients for 5 flight configurations K1_drag, K2_drag, K3_drag, K4_drag, K5_drag – Induced drag coefficients for 5 flight configurations WeightCalc This function calculates different weight parameters of the aircraft Wmax - Maximum weight (lbs) Wmin - Minimum weight (lbs) Wload - Maximum payload weight (lbs) Wgross - Gross weight (lbs) Wfuel - Fuel weight (lbs) LandingGearDrag This function calculates the landing gear drag Wnom – Nominal weight (lbs) Sref - Reference area (ft^2) Cd_gear - Landing gear drag coefficient EngineData This function maps engine thrust and fuel burn coefficients Wgross - Gross weight (lbs) MaxThrust - Max (static) thrust per engine (lbs) n_eng -Number of engines Ctc1, Ctc2, Ctc3 – Thrust coefficients Cf1, Cf2, Cf3, Cf4 – Fuel burn coefficients delta_t – Thrust precision factor (%) delta_w – Weight precision factor (%) StallSpeed This function calculates aircraft stall speed for 5 flight configurations Wmax - Maximum weight (lbs) Sref - Reference area (ft^2) V_stall - Stall speed for 5 flight configurations (knots) MaxLift This function calculates maximum lift coefficient for 5 flight configurations V_stall - Stall speed for 5 flight configurations (knots) Wmax - Maximum weight (lbs) Sref - Reference area (ft^2) CL_max - Maximum lift coefficient for 5 configurations 17 Function Purpose Input Output AC_input This function creates input file to calculate control logic gains - - Ac_file_maker_new This function calculates control logic gains AC_input data 16 Control logic coefficients GuidancePerformance This function assigns some guidance performance parameters of the aircraft AcType – Aircraft type M - Mach number Guidance performance parameters Type_rate This .mat data file is loaded by GuidancePerformance function to calculate some parameters - - WriteXML This function writes XML input file AircraftParameters data XML file (TYPEfile.xml) 2.2.3 Installing and Running The following steps outline Manual Aircraft Generator installation and running procedures: 1. Unzip file AircraftModel.zip and save all unzipped files into the same directory (for example AircraftModel) 2. Start Matlab 3. In Matlab go to File Menu and select Set Path 4. In Set Path Menu click on Add with Subfolders button and browse to find AircraftModel directory 5. Select AircraftModel directory and click OK button 6. Click Save button in Set Path Menu Steps 1-6 are implemented only once, i.e. the first time you install the tool 7. Open folder ACINPUT within AircraftModel 8. Open file ACFTparam within ACINPUT 9. Follow instructions in this document along with three provided examples for B744, B732, and MD80 to input all the required parameters (pay attention to units!) 10. Save file ACFTparam in the same folder ACINPUT as TYPEparam, where TYPE is an aircraft type under consideration (say if it is C17, save ACFTparam as C17param) 11. In Matlab command prompt type AircraftModel. Type the full path of the working directory, i.e. of AircraftModel. To find out the full path of the working directory right click on its folder and select Properties, directory’s full path will 18 be listed under Location. Do not forget to add the name of the working directory with slash to its path (Matlab command prompt will have an example). 12. Press enter and type aircraft type for which you just generated TYPEparam file (for example, C17) 13. Press enter and enter output directory name within working directory, for example OUTPUT 14. Press enter. The program will run on Pentium III – 750 MHz for about 2 seconds to generate 2 files: TYPEfile.xml and TYPEfullsim.txt in selected output directory. Steps 7-14 are implemented each time one needs to generate new aircraft model. 19 2.3 TGF Input Writer TGF Input Writer allows processing output of both BADA Processor and Manual Aircraft Generator outputs into a .xml file used in TGF. This TGF Input Writer is automatically called from within BADA Processor and Manual Aircraft Generator to generate aircraft_baseline.xml file. Currently, calling TGF Input Writer through BADA Processor will generate a .xml file containing all selected (jet, turboprop, or piston) aircraft types contained in BADA. Calling TGF Input Writer from Manual Aircraft Generator will generate a .xml file with performance data for a particular modeled aircraft. When generating aircraft_baseline.xml file it is necessary to include aircraft equivalencies statements in the beginning of the file to cover aircraft types not directly represented in BADA or not modeled manually. Aircraft Type Processor is utilized within TGF Input Writer to handle this procedure in automated fashion. Operational Enhanced Traffic Management System (ETMS) data is used to extract all aircraft types currently operating in the National Airspace System (NAS). All aircraft types directly represented in BADA or modeled manually are listed in the separate file. Other aircraft types are then matched against these models based on ref. 2 and included in the same file as synonym (equivalent) types. Aircraft types, derived from ETMS data, are compared then with BADA aircraft types. If ETMS aircraft type has an exact match with any aircraft type directly represented in BADA, then its parameters will be explicitly listed in aircraft_baseline.xml file. If ETMS aircraft type matched with BADA synonym aircraft type, then equivalence statement will be included in the beginning of aircraft_baseline.xml file. If ETMS aircraft type has no match with either aircraft types directly represented in BADA or represented in BADA through synonym types, then Manual Aircraft Generator needs to be utilized in order to generate the necessary data. The following table describes the parameters contained in aircraft_baseline.xml file, the aircraft model input file for TGF. Note that all the references (equations and figures) are made to Peters, 1999 (ref. 3). Table 3.2-1 XML File Parameters Name Var Description Units History/Revision date - Date of update - author - Author - commentary - Comment(s) (if any) - ADMAircraft aircraft_type - Aircraft designator agreed between the FAA, ICAO, NAV CANADA, and Eurocontrol - equivalent_type - Aircraft designator agreed between the FAA, ICAO, NAV CANADA, and Eurocontrol - empty_weight e W Aircraft Empty Weight lbs fuel_weight f W Aircraft Fuel Weight lbs 20 Name Var Description Units payload_weight p W Aircraft Payload Weight lbs lp p L Roll damping sec 1 la a L Ailerons effectiveness 2 sec 1 k1 ) (k k p 1 Pitch rate feedback gain sec k2 ) (k k2 ϕ Roll angle feedback gain - Engine coeff1 c,1 T C Thrust coefficient used to calculate maximum thrust in climb N coeff2 c,2 T C Thrust coefficient used to calculate maximum thrust in climb ft coeff3 c,3 T C Thrust coefficient used to calculate maximum thrust in climb 2 ft 1 f1 1f C Fuel coefficient used to calculate thrust specific fuel consumption kN min kg ⋅ f2 2f C Fuel coefficient used to calculate thrust specific fuel consumption kts f3 3f C Fuel coefficient used to calculate minimum fuel flow min kg f4 4f C Fuel coefficient used to calculate minimum fuel flow ft Airframe wing_area ref S Aircraft wing area ft2 compress 16 M C Compressibility coefficient - Cd_spoiler spoiler D C Spoilers drag coefficient - Cd_gear gear D C Landing gear drag coefficient - Cd_brakes brakes D C Brakes drag coefficient - Cd1_lift 1 D0 C Zero lift drag coefficient for Cruise flap setting - Cd2_lift 2 D0 C Zero lift drag coefficient for Initial Climb flap setting - Cd3_lift 3 D0 C Zero lift drag coefficient for Take-off flap setting - Cd4_lift 4 D0 C Zero lift drag coefficient for Approach flap setting - Cd5_lift 5 D0 C Zero lift drag coefficient for Landing flap setting - K1_drag 1 K Induced drag coefficient for Cruise flap setting - K2_drag 2 K Induced drag coefficient for Initial Climb flap setting - K3_drag 3 K Induced drag coefficient for Take-off flap setting - 21 Name Var Description Units K4_drag 4 K Induced drag coefficient for Approach flap setting - K5_drag 5 K Induced drag coefficient for Landing flap setting - CL_max1 1 Lmax C Maximum lift coefficient for Cruise flap setting - CL_max2 2 Lmax C Maximum lift coefficient for Initial Climb flap setting - CL_max3 3 Lmax C Maximum lift coefficient for Take-off flap setting - CL_max4 4 Lmax C Maximum lift coefficient for Approach flap setting - CL_max5 5 Lmax C Maximum lift coefficient for Landing flap setting - CL_min min L C Minimum lift coefficient - ControlLogic ias_error error IAS Indicate airspeed error used to define the speed-altitude plane kts mach_error error M Mach error used to define the Mach speed- altitude plane - alt_error error h Altitude error used to define the speed-altitude plane ft kh_dot h K & Altitude error gain to command an altitude rate min 1 ControlLogicGains Regions1245 R1245_Kp14 14 p k Proportional gain of PI (proportional + integral) controller (Fig 5.1) for Altitude Rate to Lift Coefficient feedback (5.7) for Regions 1, 2, 4, and 5 - R1245_Ki14 14 ik Integral gain of PI controller (Fig 5.1) for Altitude Rate to Lift Coefficient feedback (5.7) for Regions 1, 2, 4, and 5 - Regions36_MachBased R36Mach_Kb14 14 b k Feedback gain (Fig 5.1) for altitude rate (5.7) for Regions 3 and 6 Mach based - R36Mach_Kp12 12 p k Proportional gain of PI controller (Fig 5.1) for Mach Speed to Lift Coefficient feedback (5.7) for Regions 3 and 6 Mach based - R36Mach_Ki12 12 ik Integral gain of PI controller (Fig 5.1) for Mach Speed to Lift Coefficient feedback (5.7) for Regions 3 and 6 Mach based - Regions36_IasBased R36Ias_Kb14 14 b k Feedback gain (Fig 5.1) for Altitude Rate to Lift Coefficient feedback (5.7) for Regions 3 and 6 IAS (indicated airspeed) based - R36Ias_Kp11 11 p k Proportional gain of PI controller (Fig 5.1) for IAS to Lift Coefficient feedback (5.7) for Regions 3 and 6 IAS based - 22 Name Var Description Units R36Ias_Ki11 11 ik Integral gain of PI controller (Fig 5.1) for IAS to Lift Coefficient feedback (5.7) for Regions 3 and 6 IAS based - Region7_MachBased R7Mach_Kp22 22 p k Proportional gain of PI controller (Fig 5.1) for Mach Speed to Throttle feedback (5.7) for Region 7 Mach based - R7Mach_Kp14 14 p k Proportional gain of PI controller (Fig 5.1) for Altitude Rate to Lift Coefficient feedback (5.7) for Region 7 Mach based - R7Mach_Ki14 14 ik Integral gain of PI controller (Fig 5.1) for Altitude Rate to Lift Coefficient feedback (5.7) for Region 7 Mach based - R7Mach_Ki22 22 ik Integral gain of PI controller (Fig 5.1) for Mach Speed to Throttle feedback (5.7) for Region 7 Mach based - Region7_IasBased R7Ias_Kp21 21 p k Proportional gain of PI controller (Fig 5.1) for IAS to Throttle feedback (5.7) for Region 7 IAS based - R7Ias_Kp14 14 p k Proportional gain of PI controller (Fig 5.1) for Altitude Rate to Lift Coefficient feedback (5.7) for Region 7 IAS based - R7Ias_Ki14 14 ik Integral gain of PI controller (Fig 5.1) for Altitude Rate to Lift Coefficient feedback (5.7) for Region 7 IAS based - R7Ias_Ki21 21 ik Integral gain of PI controller (Fig 5.1) for IAS to Throttle feedback (5.7) for Region 7 IAS based - RegionGS_IasBased RgsIas_Kp21 21 p k Proportional gain of PI controller for IAS to Throttle feedback for Region ILS - RgsIas_Kp14 14 p k Proportional gain of PI controller for Altitude Rate to Lift Coefficient feedback for Region ILS - RgsIas_Kp13 13 p k Proportional gain of PI controller for Altitude to Lift Coefficient feedback for Region ILS - RgsIas_Ki13 13 i k Integral gain of PI controller for Altitude to Lift Coefficient feedback for Region ILS - RgsIas_Ki21 21 ik Integral gain of PI controller for IAS to Throttle feedback for Region ILS - Guidance_System Guidance_Performance_Parameters Descent_Ias con IAS V Descent IAS used in vertical constraint logic for strategies 7-9 (Chapter 10.2.2) kts Descent_Mach con M Descent Mach speed used in vertical constraint logic for strategies 7-9 (Chapter 10.2.2) - Descent_Rate_Fpm - Aircraft nominal descent rate fpm Deceleration_Rate_Mach - Aircraft Mach speed deceleration rate sec 1 23 Name Var Description Units Deceleration_Rate_Ias - Aircraft IAS deceleration rate sec kts Climb_Ias con IAS V Climb IAS used in vertical constraint logic for strategies 4-6 (Chapter 10.2.2) kts Climb_Mach con M Climb Mach speed used in vertical constraint logic for strategies 1-3 (Chapter 10.2.2) - Cruise_Ias_Low low cr, IAS V Cruise IAS at low altitudes kts Cruise_Ias_High high cr, IAS V Cruise IAS at high altitudes kts Cruise_Mach cr M Cruise Mach - Transition_Altitude_Climb climb h IAS/Mach transition altitude for climb ft Transition_Altitude_Descent descent h Mach/IAS transition altitude for descent ft 24 3 References 1. EUROCONTROL Experimental Centre (2000). User Manual for The Base of Aircraft Data (BADA). Revison 3.3 (EEC Note No. 20/00) Bretigny-sur-Orge, France. 2. EUROCONTROL Experimental Centre (1996). Equivalences Report for The Base of Aircraft Data (BADA). Revision 2.5 (EEC Note No. 30/96). Bretigny- sur-Orge, France. 3. Peters, M. (1999), The Engineering Analysis and Design of the Aircraft Dynamics Model for the FAA Target Generation Facility (working document for Federal Aviation Administration William J. Hughes Technical Center Contract No. DTFA03-94-C-00042). Atlantic City, NJ. 4. Raymer, D. (1999), Aircraft Design: A Conceptual Approach (Third Edition). American Institute of Aeronautics and Astronautics, Inc., Reston, VA. 5. Shavell, R. (1989), Fundamentals of Flight (Second Edition). Prentice Hall, Upper Saddle River, NJ. 6. Torenbeek, E. (1982), Synthesis of Subsonic Airplane Design. Delft University Press, Delft, The Netherlands. 7. Ojha, S. (1995), Flight Performance of Aircraft. American Institute of Aeronautics and Astronautics, Inc., Washington, DC. 8. Etkin, B. (1972), Dynamics of Atmospheric Flight. John Wiley & Sons, Inc., NY. 9. Frawley, G., Thorn, J. (1995/96), The International Directory of Civil Aircraft. Aerospace Publications Pty Ltd, Weston Creek, Australia. 10. Frawley, G., Thorn, J. (1996/97), The International Directory of Military Aircraft. Aerospace Publications Pty Ltd, Weston Creek, Australia. 11. Beyer, W. (1984), Standard Mathematical Tables (27th Edition). CRC Press, Inc., Boca Raton, FL. 12. U.S. Department of Transportation, Federal Aviation Administration, Aircraft Type Designators, Notice N 7110.183 13. Eurocontrol, Coverage of 2000 European Air Traffic for the Base of Aircraft Data (BADA), Revision 3.3, EEC Note No. 18/01, July 2001. 25 Appendix A BADA Operations Performance Parameters Summary A.1 Aircraft Performance Parameters Table A.1-1 BADA Aircraft Performance Parameters Model Category Symbols Units Description Aircraft Type eng n engine type wake category dimensionless string string number of engines Jet, Turboprop or Piston Heavy, Medium or Light Mass ref m min m max m pyld m tonnes tones tonnes tonnes reference mass minimum mass maximum mass maximum payload mass Flight Envelope MO V MO M MO h max h w G t G knots (CAS) dimensionless feet feet feet/kg feet/C maximum operating speed maximum operating Mach number maximum operating altitude maximum altitude at MTOW and ISA weight gradient on maximum altitude temperature gradient on maximum altitude Aerodynamics S 2 m reference wing surface area 26 Model Category Symbols Units Description CR D0, C CR D2, C AP D0, C AP D2, C LD D0, C LD D2, C LDG D0, C ∆ M16 C ( )i stall V 0) Lbo(M C = K dimensionless dimensionless dimensionless dimensionless dimensionless dimensionless dimensionless dimensionless knots (CAS) dimensionless [1/M] parasite drag coefficient (cruise) induced drag coefficient (cruise) parasite drag coefficient (approach) induced drag coefficient (approach) parasite drag coefficient (landing) induced drag coefficient (landing) parasite drag coefficient (landing gear) Mach (compressibility) drag coefficient stall speed (Take- off, Initial Climb, Cruise, Approach, Landing) buffet onset lift coefficient (jet only) buffeting gradient (jet only) Engine Thrust Tc,1 C Newton (jet/piston) 1st max climb thrust coefficient 27 Model Category Symbols Units Description Tc,2 C Tc,3 C Tc,4 C Tc,5 C low Tdes, C high Tdes, C des h app Tdes, C ld Tdes, C ref des, V ref des, M knot-Newton (turborpop) feet 2 1/ft (jet) Newton (turboprop) knot- Newton (piston) deg.C 1/deg.C dimensionless dimensionless feet dimensionless dimensionless knots dimensionless 2nd max climb coefficient 3rd max climb coefficient 1st thrust temperature coefficient 2nd thrust temperature coefficient low altitude descent thrust coefficient high altitude descent thrust coefficient transition altitude for calculation of descent thrust approach thrust coefficient landing thrust coefficient reference descent speed(CAS) reference descent Mach Fuel Flow f1 C Kg/min/kN (jet) kg/min/kN/knot (turboprop) kg/min (piston) 1st thrust specific fuel consumption coefficient 28 Model Category Symbols Units Description f2 C f3 C f4 C fcr C Knots Kg/min Feet dimensionless 2nd thrust specific fuel consumption coefficient 1st descent fuel flow coefficient 2nd descent fuel flow coefficient cruise fuel flow correction coefficient Ground Movement TOL LDL span length m m m m take-off length landing length wingspan length A.2 Airline Procedures BADA procedure models parameterize standard airline procedures for climb, cruise and descent flight phases. Airline procedures, reflected in BADA, include: • Standard climb CAS (knots) between 1,500/6,000 and 10,000 feet • Standard climb CAS (knots) between 10,000 feet and Mach transition altitude • Standard climb Mach number above Mach transition altitude • Standard cruise CAS (knots) between 3,000 and 10,000 feet • Standard cruise CAS (knots) above 10,000 ft until Mach transition altitude • Standard cruise Mach number above transition altitude • Standard descent CAS (knots) between 3,000/6,000 and 10,000 feet • Standard descent CAS (knots) above 10,000 feet until Mach transition altitude • Standard descent Mach number above transition altitude 29 A.3 Global Parameters A number of parameters in BADA have values that are independent of the aircraft type or model for which they are used. The values of these parameters are included in the General Parameters and can be changed or adjusted by the user. These parameters are listed in the following table. Table A.3-1 BADA Global Parameters Model Category Symbols Units Description Maximum Acceleration max(civ) l, a max(civ) n, a 2 fps 2 fps maximum longitudinal acceleration for civil flights maximum normal acceleration for civil flights Bank Angles LD) civ(TO, nom,  ) civ(OTHERS nom,  mil nom,  LD) civ(TO, max,  civ(HOLD) max,  ) civ(OTHERS max,  mil max,  degrees degrees degrees degrees degrees degrees degrees nominal bank angles for civil flight during TO and LD nominal bank angles for civil flight during all other phases nominal bank angles for military flight during all phases maximum bank angles for civil flight during TO and LD maximum bank angles for civil flight during HOLD maximum bank angles for civil flight during all other phases maximum bank angles for military flight during all phases 30 Model Category Symbols Units Description Expedited Descent exp des, C dimensionless expedited descent factor Thrust Factors to Th, C cr Th, C dimensionless dimensionless take-off thrust coefficient maximum cruise thrust coefficient Configuration Altitude Threshold TO max, H IC max, H AP max, H LD max, H feet feet feet feet maximum altitude threshold for take-off maximum altitude threshold for initial climb maximum altitude threshold for approach maximum altitude threshold for landing Minimum Speed Coefficients TO Vmin, C Vmin C dimensionless dimensionless minimum speed coefficient for take-off minimum speed coefficient for all other phases Speed Schedules CL,1 Vd CL,2 Vd CL,3 Vd CL,4 Vd CL,5 Vd CL,6 Vd knots knots knots knots knots knots climb speed increment below 1,500 feet (jet) climb speed increment below 3,000 feet (jet) climb speed increment below 4,000 feet (jet) climb speed increment below 5,000 feet (jet) climb speed increment below 6,000 feet (jet) climb speed increment below 500 feet (turboprop/piston) 31 Model Category Symbols Units Description CL,7 Vd CL,8 Vd DES,1 Vd DES,2 Vd DES,3 Vd DES,4 Vd DES,5 Vd DES,6 Vd DES,7 Vd knots knots knots knots knots knots knots knots knots climb speed increment below 1000 feet (turboprop/piston) climb speed increment below 1,500 feet (turboprop/piston) descent speed increment below 1,000 feet (jet/turboprop) descent speed increment below 1,500 feet (jet/turboprop) descent speed increment below 2,000 feet (jet/turboprop) descent speed increment below 3,000 feet (jet/turboprop) descent speed increment below 500 feet (piston) descent speed increment below 1,000 feet (piston) descent speed increment below 1,500 feet (piston) Holding Speed hold,1 V hold,2 V hold,3 V hold,4 V knots knots knots Mach holding speed below FL 140 holding speed between FL 140 and FL 200 holding speed between FL 200 and FL 340 holding speed above FL 340 32 Model Category Symbols Units Description Ground Speeds backtrack V taxi V apron V gate V knots knots knots knots runway backtrack speed taxi speed apron speed gate speed Reduced Power Coefficient turbo red, C piston red, C jet red, C dimensionless dimensionless dimensionless Maximum reduction in power for turboprops Maximum reduction in power for pistons Maximum reduction in power for jets 33 Appendix B BADA Sample File CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC B744__.OPF CCCCCCCCCCCCCC/ CC / CC AIRCRAFT PERFORMANCE / CC operational files / CC / CC BADA RCS File Id / CC File Name Current Revision Last Modification / CC revision date revision date / CC B744__.OPF 3.3 2000/12/06 3.1.1.1 2000/08/01 / CC / CC BADA Revision: / CD Rev 3.3 / CC====== Actype ======================================================/ CD B744__ 4 engines Jet H / CC B747-400 with CF6_80C2B1F engines wake / CC (source = Air France OPS manual) / CC====== Mass (t) ====================================================/ CC reference minimum maximum max payload mass grad / CD .30000E+03 .18000E+03 .37200E+03 .61640E+02 .60000E-01 / CC====== Flight envelope =============================================/ CC VMO(KCAS) MMO Max.Alt Hmax temp grad / CD .36500E+03 .90000E+00 .45000E+05 .35400E+05 -.20000E+03 / CC====== Aerodynamics ================================================/ CC Wing Area and Buffet coefficients (SIM) / CCndrst Surf(m2) Clbo(M=0) k CM16 / CD 5 .51200E+03 .99000E+00 .33500E+00 .00000E+00 / CC Configuration characteristics / CC n Phase Name Vstall(KCAS) CD0 CD2 unused / CD 1 CR Clean .18000E+03 .22000E-01 .45000E-01 .00000E+00 / CD 2 IC Flap05 .14900E+03 .00000E+00 .00000E+00 .00000E+00 / CD 3 TO Flap20 .14000E+03 .00000E+00 .00000E+00 .00000E+00 / CD 4 AP Flap20 .14000E+03 .00000E+00 .00000E+00 .00000E+00 / CD 5 LD Flap30 .12800E+03 .00000E+00 .00000E+00 .00000E+00 / CC Spoiler / CD 1 RET / CD 2 EXT .00000E+00 .00000E+00 / CC Gear / CD 1 UP / CD 2 DOWN .00000E+00 .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 .62668E+06 .59557E+05 .00000E+00 .30258E+01 .42770E-02 / CC Desc(low) Desc(high) Desc level Desc(app) Desc(ld) / CD .12247E+00 .79764E-01 .20000E+05 .00000E+00 .00000E+00 / CC Desc CAS Desc Mach unused unused unused / CD .28000E+03 .85000E+00 .00000E+00 .00000E+00 .00000E+00 / CC====== Fuel Consumption ============================================/ CC Thrust Specific Fuel Consumption Coefficients / CD .86709E+00 .53904E+04 / CC Descent Fuel Flow Coefficients / CD .39007E+02 .75715E+05 / CC Cruise Corr. unused unused unused unused / CD .89880E+00 .00000E+00 .00000E+00 .00000E+00 .00000E+00 / CC====== Ground ======================================================/ CC TOL LDL span length unused / CD .33200E+04 .21300E+04 .64300E+02 .70700E+02 .00000E+00 / CC====================================================================/ FI 34 Appendix C Aircraft Equivalents Table C-1 Aircraft Types and Equivalents Aircraft Type Modeled in BADA Cat Equivalents A306 J A306 A300 A30B J A30B IL76 A310 J A310 A319 J A319 A320 J A320 A321 J A321 A330 J A330 A340 J A340 AT43 T AT43 AT44 AT45 ATR AT72 T AT72 A748 ATP T ATP E2 B703 J B701 B703 B707 B720 C135 K35A K35E K35R R135 E3TF E3CF E3 E6 KE3 VC10 IL62 B722 J B721 B722 B72Q B727 TRID COMT CV99 B732 J B712 B731 B732 B73Q B73A B733 J B733 B734 B735 B73B B73S B738 J B736 B737 B738 B73C B742 J B741 B742 B743 C5 B747 B744 J B52 B744 B74R B74A B74B B74S C17 B1 B752 J B752 B753 B757 B763 J B762 B763 B767 B772 J B772 B773 B777 BA11 J BA11 BA46 J AR7 BA46 BE20 T B350 BE20 BE30 STAR N260 N262 AC6T BE99 T TBM7 BE99 T34T BN2T C208 DH2T DHC6 D28T G64T STLN P68T VTOR PC7 PC12 AC80 SC7 F26T BE90 BE9L T BE10 BE9L U21 B18T V10 F600 C130 T SGUP VISC DHC7 C130 L188 P3 C160 T C160 C421 P C97 BU20 C320 C404 C411 C414 C421 L18 AC95 C550 J S601 BE40 C500 C501 C525 C526 C550 C551 C750 T37 HF20 MU30 C560 J C560 CL60 J CL60 GLF2 GLF3 GLF4 GLF5 GULF L29A L29B 35 Aircraft Type Modeled in BADA Cat Equivalents CRJ1 J CARJ E145 D228 T D228 E110 D328 T D328 G159 DC10 J DC10 KC10 DC87 J C141 DC85 DC86 DC87 DC8Q DC8 DC9 J DC9 DH8C T F406 DHC5 DH8A DH8B DH8C DHC8 PC6T CVLT C2 YS11 DH8 CV58 E120 T E120 F100 J S210 F100 VF14 F27 T F27 F28 J F28 F50 T F50 F60 F70 J F70 F900 J F900 FA10 J FA10 FA20 J FA20 F2TH ASTR P808 JCOM SBR1 FA50 J FA50 FGTR J CONC HAR A37 A10 F111 F16 A6 F14 F104 S3 R33 TR1 U2 A3 A4 F15 F18 F4 F5 T38 F86 SSAB T2 A7 H25B J H25A H25B H25C WW23 WW24 JS31 T B190 JS1 JS20 JS3 JS31 JS32 JSTA V1 JS1 JS20 JSTA JS41 T JS41 JSTB L101 J L101 LJ35 J C650 LJ23 LJ24 LJ25 LJ28 LJ31 LJ35 LJ60 MD11 J MD11 MD80 J MD80 MD90 J MD90 MU2 T C441 M7T MU2 P28A P RALL TAMP TOBA ERCO PUP BE19 BE23 BE24 B14A BL17 BL8 CH7A CH7B C120 C140 C150 C152 C170 C172 C72R C175 C177 C77R C180 C182 C82R C185 C188 C190 C195 C205 C206 C207 C210 P210 O1 DHC1 DHC2 DHC3 DHC4 DV20 DO27 E200 E230 E300 E400 FA62 PC6P CAT VALI G109 G115 AA1 AA5 G164 COUR DG15 LA25 LA4 M4 M5 M6 M7 B209 RANG NORS OSCR PA11 PA12 PA14 PA15 PA16 PA17 PA18 PA20 PA22 PA24 PA25 P28A PA8B PA28 P28T PA32 P32R P32T PA36 PA38 PA46 PAT4 PA42 PILL S108 AC11 CM11 LARK T6 VO10 R90F R90R L8 L5 RELI S10 S108 TA15 TF19 TA20 TF21 GC1 CH2T PA27 P BE50 BE55 BE58 HUSK DOVE P66P AEST PA23 PA27 C310 36 Aircraft Type Modeled in BADA Cat Equivalents AEST PA31 P CP10 CP20 BE60 BE65 BE76 BE77 BE80 BE95 BN2P TRIS TNAV C303 C310 C335 C340 C402 HERN DO28 D28D G21 G44 G73 GA7 U16 M404 TNAV NORA PA30 PA31 PTS1 PTS2 P51 T28 PA34 P BASS BE17 BE18 BE33 BE35 BE36 T34P CH40 C336 C337 P337 C46 C119 C123 CVLP TCOU CONI B26 DC3 DC3S DC4 DC6 DC7 P68 P136 PA34 PA44 AC50 AC52 AC56 AC68 AC6L AC72 B25 M200 PAY2 T C425 P46T PAY1 PAY2 P31T PAY3 T PAY3 PAY4 AC90 SF34 T SF34 SH36 T C212 ARVA PC6T SH33 SH36 SW3 T SW2 SW3 SW4 TRIN P TRIN AT3P AR11 AR15 ST75 ME08 MITE M10 M20P M20T M20 M22 PC6P P28R NAVI J2 J3 J4 J5 37 Appendix D Sample Input File %This file contains data for Boeing 747-400 with CF6-80C2B4 engines %Aircraft type designator per FAA/ICAO/NAV CANADA and Eurocontrol AcType = 'B744'; EngType = 'jet'; %Cruise flight conditions h = 35000; % Cruise altitude (ft) hmax = 45000; % Max altitude (ft), operating ceiling M = 0.85; % Cruise Mach %Weight data Wmax = 372*1000/.454; % Aircraft maximum take-off weight (lbs) Wnom = 300*1000/.454; % Aircraft nominal weight (lbs) Wmin = 180*1000/.454; % Aircraft operating empty weight (lbs) Wload = 61.64*1000/.454; % Aircraft maximum payload weight (lbs)) %Wing data Sref = 525*10.7626; % Wing plan form area (ft^2) AR = 7.39; % Aspect ratio lambda = 0.275; % Taper ratio SWEEPq = 37.5; % 1/4 Chord sweep (deg) t_c = 9.40/100; % Thickness ratio h_wlt = 0; % Winglet height (ft), 0 (no winglets) %Fuselage data Df = 8.10*3.2808; % Fuselage diameter (ft) Lf = 68.63*3.2808; % Fuselage length (ft) Lnf = 0.2*Lf; % Fuselage nose section length (ft) Ltf = 0.3*Lf; % Fuselage tail section length (ft) %Horizontal Tail data S_ht = 136.6*10.7626; % Horizontal tail plan form area (ft^2) AR_ht = 3.57; % Aspect ratio lambda_ht = 0.265; % Taper ratio SWEEPq_ht = 32; % 1/4 Chord sweep (deg) t_c_ht = t_c; % Thickness ratio %Vertical Tail data S_vt = 77.10*10.7626; % Vertical tail plan form area (ft^2) AR_vt = 1.34; % Aspect ratio lambda_vt = 0.330; % Taper ratio SWEEPq_vt = 45; % 1/4 Chord sweep (deg) t_c_vt = t_c; % Thickness ratio %Engine data n_eng = 4; % Number of engines Dn = 2.9*3.2808; % Nacelle diameter (ft) Ln = 5.64*3.2808; % Nacelle length (ft) MaxThrust = 57900; % Maximum (static) thrust per engine (lbs) 38 Appendix E Sample XML Output File -<ADMAircraft> <aircraft_type>B744</aircraft_type> <empty_weight>3.9672000e+005</empty_weight> <fuel_weight>2.8731344e+005</fuel_weight> <payload_weight>1.3585456e+005</payload_weight> <lp>0.475</lp> <la>0.185</la> <k1>22.0</k1> <k2>50.0</k2> -<Engine> -<Jet> <coeff1>6.2668000e+005</coeff1> <coeff2>5.9557000e+004</coeff2> <coeff3>0.0000000e+000</coeff3> <f1>8.6709000e-001</f1> <f2>5.3904000e+003</f2> <f3>3.9007000e+001</f3> <f4>7.5715000e+004</f4> </Jet> </Engine> -<Airframe> <wing_area>5.5091200e+003</wing_area> <compress>6.0000000e+000</compress> <Cd_spoiler>0.0000000e+000</Cd_spoiler> <Cd_gear>1.7038127e-002</Cd_gear> <Cd_brakes>0.0000000e+000</Cd_brakes> <Cd1_lift>2.2000000e-002</Cd1_lift> <Cd2_lift>2.7964200e-002</Cd2_lift> <Cd3_lift>3.2865800e-002</Cd3_lift> <Cd4_lift>4.1516200e-002</Cd4_lift> <Cd5_lift>7.5922000e-002</Cd5_lift> <K1_drag>4.5000000e-002</K1_drag> <K2_drag>4.3591500e-002</K2_drag> <K3_drag>4.0810500e-002</K3_drag> <K4_drag>4.0531500e-002</K4_drag> <K5_drag>3.8772000e-002</K5_drag> <CL_max1>1.3625436e+000</CL_max1> <CL_max2>1.9884876e+000</CL_max2> <CL_max3>2.2523680e+000</CL_max3> <CL_max4>2.2523680e+000</CL_max4> <CL_max5>2.6944832e+000</CL_max5> <CL_min>0.0000000e+000</CL_min> </Airframe> -<ControlLogic> <ias_error>10.0</ias_error> <mach_error>0.0151</mach_error> <alt_error>500.0</alt_error> <kh_dot>7.0</kh_dot> -<ControlLogicGains> -<Regions1245> <R1245_Kp14>1.6061020e-004</R1245_Kp14> <R1245_Ki14>2.0935634e-005</R1245_Ki14> </Regions1245> -<Regions36_MachBased> 39 <R36Mach_Kb14>1.6977551e-004</R36Mach_Kb14> <R36Mach_Kp12>-5.7207608e+001</R36Mach_Kp12> <R36Mach_Ki12>-5.4633643e+000</R36Mach_Ki12> </Regions36_MachBased> -<Regions36_IasBased> <R36Ias_Kb14>1.6977551e-004</R36Ias_Kb14> <R36Ias_Kp11>-9.9641423e-002</R36Ias_Kp11> <R36Ias_Ki11>-9.5158216e-003</R36Ias_Ki11> </Regions36_IasBased> -<Region7_MachBased> <R7Mach_Kp22>4.8205992e+006</R7Mach_Kp2> <R7Mach_Kp14>1.7700000e-004</R7Mach_Kp14> <R7Mach_Ki14>1.8430013e-005</R7Mach_Ki14> <R7Mach_Ki22>7.3224471e+005</R7Mach_Ki22> </Region7_MachBased> -<Region7_IasBased> <R7Ias_Kp21>8.3962846e+003</R7Ias_Kp21> <R7Ias_Kp14>1.7700000e-004</R7Ias_Kp14> <R7Ias_Ki14>1.8430013e-005</R7Ias_Ki14> <R7Ias_Ki21>1.2753881e+003</R7Ias_Ki21> </Region7_IasBased> -<RegionGS_IasBased> <RgsIas_Kp21>3.1520701e+004</RgsIas_Kp21> <RgsIas_Kp14>1.0633606e-003</RgsIas_Kp14> <RgsIas_Kp13>3.0838633e-002</RgsIas_Kp13> <RgsIas_Ki13>2.6145686e-003</RgsIas_Ki13> <RgsIas_Ki21>8.0044333e+003</RgsIas_Ki21> </RegionGS_IasBased> </ControlLogicGains> </ControlLogic> -<Guidance_System> -<Guidance_Performance_Parameters> <Descent_Ias>280</Descent_Ias> <Descent_Mach>0.85</Descent_Mach> <Descent_Rate_Fpm>1800</Descent_Rate_Fpm> <Deceleration_Rate_Mach>0.001667</Deceleration_Ra te_Mach> <Deceleration_Rate_Ias>1</Deceleration_Rate_Ias> <Climb_Ias>340</Climb_Ias> <Climb_Mach>0.85</Climb_Mach> <Cruise_Ias_Low>250</Cruise_Ias_Low> <Cruise_Ias_High>340</Cruise_Ias_High> <Cruise_Mach>0.85</Cruise_Mach> <Transition_Altitude_Climb>27861</Transition_Alti tude_Climb> <Transition_Altitude_Descent>36672</Transition_Al titude_Descent> </Guidance_Performance_Parameters> </Guidance_System> </ADMAircraft>