Sample: JetSample.asm
JetSample.asm |
| ; Copyright (c) Microsoft Corporation. All rights reserved. ; Sample Jet flight dynamics file ; ; include asm.inc ; include this in ALL .asm files! include airtoken.inc ; definitions of token macros include sim1.inc ; definitions of token values .data sim_data label byte ;******START OF AERODYNAMIC DATA ************************************************************************************ ;******************************************************************************************************************** ;**** BEGINNING OF REQUIRED AERODYNAMICS ************************ ;The following 6 blocks define the base stability and control derivatives ;Lift, Drag, Pitch, Side Force, Roll, and Yaw. TOKEN_BEGIN AIR_80_LIFT_PARAMS REAL8 -0.480000 ; CL spoiler REAL8 0.491244 ; CL flaps REAL8 0.000000 ; UNUSED REAL8 0.353935 ; CLih REAL8 -0.134961 ; CLde REAL8 0.000000 ; UNUSED TOKEN_END TOKEN_BEGIN AIR_80_DRAG_PARAMS REAL8 0.051 ; CDo REAL8 0.080000 ; CD flaps REAL8 0.007000 ; CD gear REAL8 0.130000 ; CD spoiler TOKEN_END TOKEN_BEGIN AIR_80_PITCH_PARAMS REAL8 -1.423802 ; CMih REAL8 -1.4 ; CMde REAL8 0.000000 ; CMde due to propwash REAL8 -3.966478 ; CLq REAL8 0.770403 ; CL adot REAL8 5.099159 ; CM adot REAL8 -91.0 ; CMq REAL8 0.000000 ; CMq due to propwash REAL8 -0.02 ; CMo REAL8 -0.002 ; CM flap REAL8 -7.119009 ; CM delta trim REAL8 0.00000 ; CM gear REAL8 0.010000 ; CM spoiler TOKEN_END TOKEN_BEGIN AIR_80_SIDE_FORCE_PARAMS REAL8 -0.678522 ; CyB REAL8 0.029355 ; CyP REAL8 0.061966 ; CyR REAL8 -0.193005 ; Cy Delta Rudder TOKEN_END TOKEN_BEGIN AIR_80_ROLL_PARAMS REAL8 0.157221 ; ClB REAL8 -4.134894 ; ClP REAL8 -0.162191 ; ClR REAL8 0.123552 ; Cl Delta Spoiler REAL8 -0.197583 ; Cl Delta Aileron REAL8 0.024785 ; Cl Delta Rudder TOKEN_END TOKEN_BEGIN AIR_80_YAW_PARAMS REAL8 0.322632 ; CnB REAL8 0.210647 ; CnP REAL8 -2.520723 ; CnR REAL8 0.000000 ; CnR due to propwash REAL8 0.000000 ; UNUSED REAL8 0.000000 ; UNUSED REAL8 -0.002180 ; Cn Delta Aileron REAL8 0.116691 ; Cn Delta Rudder REAL8 0.000000 ; Cn Delta Rudder due to propwash TOKEN_END ;CL vs. Alpha ;The first entry defines the number of data points (maximum 47 entries) TOKEN_BEGIN AIR_CL_ALPHA dd 13 ; Number of Entries REAL8 -3.142, 0.000 REAL8 -2.356, 0.500 REAL8 -1.571, 0.000 REAL8 -0.344, -1.338 REAL8 -0.065, 0.000 REAL8 0.000, 0.384 REAL8 0.244, 1.836 REAL8 0.279, 1.912 REAL8 0.314, 1.836 REAL8 0.349, 1.338 REAL8 1.571, 0.000 REAL8 2.356, -0.500 REAL8 3.142, 0.000 TOKEN_END ;CM vs. Alpha ;The first entry defines the number of data points (maximum 47 entries) TOKEN_BEGIN AIR_CM_ALPHA dd 13 ; Number of Entries REAL8 -3.142, 0.000 REAL8 -0.541, -0.528 REAL8 -0.367, -0.528 REAL8 -0.297, -0.264 REAL8 -0.279, -0.220 REAL8 -0.262, -0.183 REAL8 0.000, 0.000 REAL8 0.262, 0.183 REAL8 0.279, 0.220 REAL8 0.297, 0.264 REAL8 0.367, 0.528 REAL8 0.541, 0.528 REAL8 3.142, 0.000 TOKEN_END ;**** END OF REQUIRED AERODYNAMICS ************************************************ ;**** GROUND EFFECT ************************ ;Scalar on Lift due to ground proximity (max 11 entries) ;IN: Ratio of wingspan / height above ground ;OUT: Scalar on CL TOKEN_BEGIN AIR_GROUND_EFFECT dd 11 ; Number of Entries REAL8 0.054000, 1.250000 ; REAL8 0.100000, 1.160000 ; REAL8 0.200000, 1.096100 ; REAL8 0.300000, 1.060000 ; REAL8 0.400000, 1.040000 ; REAL8 0.500000, 1.030000 ; REAL8 0.600000, 1.024200 ; REAL8 0.700000, 1.021300 ; REAL8 0.800000, 1.016100 ; REAL8 0.900000, 1.010000 ; REAL8 1.000000, 1.000000 ; TOKEN_END ;**** END OF GROUND EFFECT ************************ ;**** BEGINNING OF ADDITIONAL CONTROL EFFECTS ************* ;Scalar affect of aileron and rudder trim ;0 implies no trim TOKEN_BEGIN AIR_61S_AIL_RUD_TRIM_CONSTANTS REAL8 -0.2 ;cl_delta_ailertrim REAL8 0.2 ;cn_delta_rudtrim TOKEN_END ;Elevator effectiveness scaling table (max 7 entries) ; IN: Elevator angle (radians) ; OUT: Effectiveness scalar TOKEN_BEGIN AIR_ELEVATOR_SCALING UINT32 7 ;NUMBER OF ENTRIES REAL8 -0.349, 1.0 ;-20 DEG REAL8 -0.262, 1.0 ;-15 DEG REAL8 -0.175, 1.0 ;-10 DEG REAL8 0.0, 1.0 REAL8 0.175, 1.0 ;10 DEG REAL8 0.262, 1.0 ;15 DEG REAL8 0.296, 1.0 ;17 DEG TOKEN_END ;Aileron effectiveness scaling table (max 7 entries) ; IN: Aileron angle (radians) ; OUT: Effectiveness scalar TOKEN_BEGIN AIR_AILERON_SCALING UINT32 7 ;NUMBER OF ENTRIES REAL8 -0.785, 1.0 ;-45 DEG REAL8 -0.524, 1.0 ;-30 DEG REAL8 -0.175, 1.0 ;-10 DEG REAL8 0.0, 1.0 REAL8 0.175, 1.0 ;10 DEG REAL8 0.524, 1.0 ;30 DEG REAL8 0.785, 1.0 ;45 DEG TOKEN_END ;Rudder effectiveness scaling table (max 7 entries) ; IN: Rudder angle (radians) ; OUT: Effectiveness scalar TOKEN_BEGIN AIR_RUDDER_SCALING UINT32 7 ;NUMBER OF ENTRIES REAL8 -0.785, 1.0 ;-45 DEG REAL8 -0.524, 1.0 ;-30 DEG REAL8 -0.175, 1.0 ;-10 DEG REAL8 0.0, 1.0 REAL8 0.175, 1.0 ;10 DEG REAL8 0.524, 1.0 ;30 DEG REAL8 0.785, 1.0 ;45 DEG TOKEN_END ;Elevator elasticity on effectiveness scaling table (max 5 entries) ; IN: Aircraft dynamic pressure ( 1/2 Rho * V^2) (psf) ; OUT: Effectiveness scalar TOKEN_BEGIN AIR_61S_ELEVATOR_ELASTICITY UINT32 5 ;NUMBER OF ENTRIES ;q=.5rhoV^2 REAL8 0.0, 1.0 ;Ve = 0 keas REAL8 135.0, 1.0 ;Ve = 200 keas REAL8 300.0, 1.0 ;Ve = 297 keas REAL8 1000.0, 0.8 ;Ve = 543 keas REAL8 1500.0, 0.4 ;Ve = 665 keas TOKEN_END ;Elevator trim elasticity on effectiveness scaling table (max 5 entries) ; IN: Aircraft dynamic pressure ( 1/2 Rho * V^2) (psf) ; OUT: Effectiveness scalar TOKEN_BEGIN AIR_70_ELEVATOR_TRIM_ELASTICITY UINT32 5 ;NUMBER OF ENTRIES ;q=.5rhoV^2 REAL8 0.0, 1.0 ;Ve = 0 keas REAL8 300.0, 0.4 ;Ve = 297 keas REAL8 800.0, 0.2 ;Ve = 485 keas REAL8 1000.0, 0.2 ;Ve = 543 keas REAL8 1500.0, 0.1 ;Ve = 665 keas TOKEN_END ;Aileron elasticity on effectiveness scaling table (max 5 entries) ; IN: Aircraft dynamic pressure ( 1/2 Rho * V^2) (psf) ; OUT: Effectiveness scalar TOKEN_BEGIN AIR_61S_AILERON_ELASTICITY UINT32 5 ;NUMBER OF ENTRIES ;q=.5rhoV^2 REAL8 0.0, 1.0 ;Ve = 0 keas REAL8 300.0, 0.5 ;Ve = 297 keas REAL8 600.0, 0.2 ;Ve = 420 keas REAL8 1482.0, 0.1 ;Ve = 760 keas REAL8 1500.0, 0.1 ;Ve = 665 keas TOKEN_END ;Rudder elasticity on effectiveness scaling table (max 5 entries) ; IN: Aircraft dynamic pressure ( 1/2 Rho * V^2) (psf) ; OUT: Effectiveness scalar TOKEN_BEGIN AIR_61S_RUDDER_ELASTICITY UINT32 5 ;NUMBER OF ENTRIES ;q=.5rhoV^2 REAL8 0.0, 1.0 ;Ve = 0 keas REAL8 300.0, 1.0 ;Ve = 297 keas REAL8 800.0, 0.5 ;Ve = 485 keas REAL8 1000.0, 0.3 ;Ve = 543 keas REAL8 1500.0, 0.2 ;Ve = 665 keas TOKEN_END ;Load factor on effectiveness scaling table (max 5 entries) ; IN: Aircraft load factor ; OUT: Effectiveness scalar TOKEN_BEGIN AIR_61S_AILERON_LOAD_FACTOR_EFF dd 5 ; Number of Entries REAL8 0.000000, 1.0 ; REAL8 3.000000, 1.0 ; REAL8 4.000000, 1.0 ; REAL8 6.000000, 1.0 ; REAL8 8.000000, 1.0 ; TOKEN_END ;**** END OF ADDITIONAL CONTROL EFFECTS ************* ;**** START OF ANGLE OF ATTACK TABLES *************** ;Cl (roll) induced by angle of attack (max 7 entries) ; IN: Angle of attack (degrees) ; OUT: Delta Cl TOKEN_BEGIN AIR_70S_Cl_ALPHA_ROLL UINT32 7 ;NUMBER OF ENTRIES REAL8 -17.0, 0.00 REAL8 -10.0, 0.00 REAL8 -6.0, 0.00 REAL8 10.0, 0.00 REAL8 12.0, 0.00 REAL8 13.0, 0.00 REAL8 17.0, 0.00 TOKEN_END ;Cn (yaw) induced by angle of attack (max 7 entries) ; IN: Angle of attack (degrees) ; OUT: Delta Cn TOKEN_BEGIN AIR_70S_CN_ALPHA_YAW UINT32 7 ;NUMBER OF ENTRIES REAL8 -16.0, 0.00 REAL8 -13.0, 0.00 REAL8 -10.0, 0.00 REAL8 10.0, 0.00 REAL8 11.0, 0.00 REAL8 13.0, 0.00 REAL8 15.0, 0.00 TOKEN_END ;Scalar on Cmde due to angle of attack (max 5 entries) ; IN: Angle of attack (degrees) ; OUT: Scalar on Cmde TOKEN_BEGIN AIR_61S_ALPHA_ON_CMDE dd 5 ; Number of Entries REAL8 -15.000000, 1.00000 ; REAL8 0.000000, 1.00000 ; REAL8 8.000000, 1.00000 ; REAL8 15.000000, 1.00000 ; REAL8 20.000000, 1.00000 ; TOKEN_END ;Scalar on Cmih due to angle of attack (max 5 entries) ; IN: Angle of attack (degrees) ; OUT: Scalar on Cmih TOKEN_BEGIN AIR_61S_ALPHA_ON_CMIH dd 5 ; Number of Entries REAL8 -15.000000, 1.000000 ; REAL8 0.000000, 1.000000 ; REAL8 13.000000, 1.000000 ; REAL8 15.000000, 1.000000 ; REAL8 25.000000, 1.000000 ; TOKEN_END ;Scalar on Cmadot due to angle of attack (max 5 entries) ; IN: Angle of attack (degrees) ; OUT: Scalar on Cmadot TOKEN_BEGIN AIR_61S_ALPHA_ON_CMADOT dd 5 ; Number of Entries REAL8 -15.000000, 1.000000 ; REAL8 0.000000, 1.000000 ; REAL8 5.000000, 1.000000 ; REAL8 15.000000, 1.000000 ; REAL8 25.000000, 1.000000 ; TOKEN_END ;Scalar on Cmq due to angle of attack (max 5 entries) ; IN: Angle of attack (degrees) ; OUT: Scalar on Cmq TOKEN_BEGIN AIR_61S_ALPHA_ON_CMQ dd 5 ; Number of Entries REAL8 -15.000000, 1.000000 ; REAL8 0.000000, 1.000000 ; REAL8 11.000000, 1.000000 ; REAL8 15.000000, 1.000000 ; REAL8 25.000000, 1.000000 ; TOKEN_END ;Scalar on Cndr due to angle of attack (max 5 entries) ; IN: Angle of attack (degrees) ; OUT: Scalar on Cndr TOKEN_BEGIN AIR_70S_ALPHA_ON_CNDR dd 5 ; Number of Entries REAL8 -15.000000, 1.000000 ; REAL8 0.000000, 1.000000 ; REAL8 11.000000, 1.000000 ; REAL8 15.000000, 1.000000 ; REAL8 25.000000, 1.000000 ; TOKEN_END ;Scalar on Clda due to angle of attack (max 5 entries) ; IN: Angle of attack (degrees) ; OUT: Scalar on Clda TOKEN_BEGIN AIR_70S_ALPHA_ON_CLDA dd 5 ; Number of Entries REAL8 -15.000000, 1.000000 ; REAL8 0.000000, 1.000000 ; REAL8 11.000000, 1.000000 ; REAL8 15.000000, 1.000000 ; REAL8 25.000000, 1.000000 ; TOKEN_END ;Scalar on ClBeta due to angle of attack (max 9 entries) ; IN: Angle of attack (degrees) ; OUT: Scalar on ClBeta TOKEN_BEGIN AIR_ALPHA_ON_CL_BETA dd 9 ; Number of Entries REAL8 -180.000000, 1.000000 ; REAL8 -90.000000, 1.000000 ; REAL8 -15.000000, 1.000000 ; REAL8 -10.000000, 1.000000 ; REAL8 0.000000, 1.000000 ; REAL8 10.000000, 1.000000 ; REAL8 15.000000, 1.000000 ; REAL8 90.000000, 1.000000 ; REAL8 180.000000, 1.000000 ; TOKEN_END ;Scalar on Clp due to angle of attack (max 9 entries) ; IN: Angle of attack (degrees) ; OUT: Scalar on Cmp TOKEN_BEGIN AIR_ALPHA_ON_CLP dd 9 ; Number of Entries REAL8 -180.0, 1.0 REAL8 -90.0, 0.3 REAL8 -18.0, 0.4 REAL8 -10.0, 0.6 REAL8 0.0, 1.0 REAL8 10.0, 0.6 REAL8 18.0, 0.4 REAL8 90.0, 0.3 REAL8 180.0, 1.0 TOKEN_END ;Scalar on CnBeta due to angle of attack (max 9 entries) ; IN: Angle of attack (degrees) ; OUT: Scalar on CnBeta TOKEN_BEGIN AIR_ALPHA_ON_CN_BETA dd 9 ; Number of Entries REAL8 -180.0, 1.0 REAL8 -90.0, 0.0 REAL8 -18.0, 0.2 REAL8 -10.0, 0.3 REAL8 0.0, 1.0 REAL8 10.0, 0.3 REAL8 18.0, 0.2 REAL8 90.0, 0.0 REAL8 180.0, 1.0 TOKEN_END ;Scalar on Cnr due to angle of attack (max 9 entries) ; IN: Angle of attack (degrees) ; OUT: Scalar on Cnr TOKEN_BEGIN AIR_ALPHA_ON_CNR dd 9 ; Number of Entries REAL8 -180.0, 1.0 REAL8 -90.0, 0.1 REAL8 -18.0, 0.2 REAL8 -10.0, 0.4 REAL8 0.0, 1.0 REAL8 10.0, 0.4 REAL8 18.0, 0.2 REAL8 90.0, 0.1 REAL8 180.0, 1.0 TOKEN_END ;**** END OF ANGLE OF ATTACK TABLES *************** ;**** START OF MACH TABLES *************** ;Scalar on Lift due to mach (max 17 entries) ;IN: Mach ;OUT: Scalar on CL0 TOKEN_BEGIN AIR_CL_MACH UINT32 17 REAL8 0.0, 1.0000 REAL8 0.2, 1.0000 REAL8 0.4, 1.0369 REAL8 0.6, 1.1018 REAL8 0.8, 1.2687 REAL8 1.0, 0.6000 REAL8 1.2, 0.5000 REAL8 1.4, 0.4000 REAL8 1.6, 0.4000 REAL8 1.8, 0.4000 REAL8 2.0, 0.4000 REAL8 2.2, 0.3968 REAL8 2.4, 0.3571 REAL8 2.6, 0.3373 REAL8 2.8, 0.3274 REAL8 3.0, 0.3274 REAL8 3.2, 0.3274 TOKEN_END ;Scalar on Drag due to mach (max 17 entries) ;IN: Mach ;OUT: Delta CD0 due to mach TOKEN_BEGIN AIR_10XPACK_CD0_MACH UINT32 17 ;NUMBER OF ENTRIES ;Mach ;Delta CD0 REAL8 0.00, 0.0000 REAL8 0.20, 0.0000 REAL8 0.54, 0.0020 REAL8 0.66, 0.0034 REAL8 0.77, 0.0177 REAL8 0.84, 0.0203 REAL8 0.91, 0.0226 REAL8 0.97, 0.0243 REAL8 1.09, 0.0254 REAL8 1.32, 0.0251 REAL8 1.48, 0.0238 REAL8 1.73, 0.0170 REAL8 2.40, 0.0114 REAL8 2.60, 0.0101 REAL8 2.80, 0.0098 REAL8 3.00, 0.0098 REAL8 3.20, 0.0098 TOKEN_END ;************************************************************************************** ; The following mach data tables are fixed size (17 elements) and are assumed to have ; inputs of Mach from 0.0 to 3.2, where each table step is 0.2 Mach. The output is ; an integer which is the scalar multiplied by 2^11, or 2048. E.g. a desired about of ; 0.25 would be configured in the table as 512. All outputs are additive to the base ; aerodynamic coefficient. ;************************************************************************************** ;Integer mach table on Clde ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Clde due to mach TOKEN_BEGIN AIR_CL_DELTAE dw 0 ;0.0 dw 0 ;0.2 dw -21 ;0.4 dw -82 ;0.6 dw -246 ;0.8 dw -246 ;1.0 dw -205 ;1.2 dw -164 ;1.4 dw -123 ;1.6 dw -82 ;1.8 dw -41 ;2.0 dw -41 ;2.2 dw -41 ;2.4 dw -41 ;2.6 dw -41 ;2.8 dw -41 ;3.0 dw -41 ;3.2 TOKEN_END ;Integer mach table on Cladot ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cladot due to mach TOKEN_BEGIN AIR_CL_ADOT dw 0 ;0.0 dw 0 ;0.2 dw 410 ;0.4 dw 1024 ;0.6 dw 2253 ;0.8 dw 3482 ;1.0 dw 2253 ;1.2 dw 1024 ;1.4 dw 410 ;1.6 dw 410 ;1.8 dw 410 ;2.0 dw 410 ;2.2 dw 410 ;2.4 dw 410 ;2.6 dw 410 ;2.8 dw 410 ;3.0 dw 410 ;3.2 TOKEN_END ;Integer mach table on CLq ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta CLq due to mach TOKEN_BEGIN AIR_CL_Q dw 0 ;0.0 dw 0 ;0.2 dw -410 ;0.4 dw -1024 ;0.6 dw -2458 ;0.8 dw -2458 ;1.0 dw -1024 ;1.2 dw -410 ;1.4 dw 0 ;1.6 dw 0 ;1.8 dw 0 ;2.0 dw 0 ;2.2 dw 0 ;2.4 dw 0 ;2.6 dw 0 ;2.8 dw 0 ;3.0 dw 0 ;3.2 TOKEN_END ;Integer mach table on Clih ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Clih due to mach TOKEN_BEGIN AIR_CL_IH dw 0 ;0.0 dw 0 ;0.2 dw 20 ;0.4 dw 82 ;0.6 dw 328 ;0.8 dw 328 ;1.0 dw 328 ;1.2 dw 328 ;1.4 dw 328 ;1.6 dw 328 ;1.8 dw 328 ;2.0 dw 328 ;2.2 dw 328 ;2.4 dw 328 ;2.6 dw 328 ;2.8 dw 328 ;3.0 dw 328 ;3.2 TOKEN_END ;Integer mach table on Cmde ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cmde due to mach TOKEN_BEGIN AIR_CM_DELTAE dw 0 ;0.0 dw -20 ;0.2 dw -82 ;0.4 dw -163 ;0.6 dw -318 ;0.8 dw -207 ;1.0 dw -205 ;1.2 dw -102 ;1.4 dw 0 ;1.6 dw 51 ;1.8 dw 102 ;2.0 dw 102 ;2.2 dw 102 ;2.4 dw 102 ;2.6 dw 102 ;2.8 dw 102 ;3.0 dw 102 ;3.2 TOKEN_END ;Integer mach table on Cmadot ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cmadot due to mach TOKEN_BEGIN AIR_CM_ADOT dw 0 ;0.0 dw 51 ;0.2 dw 205 ;0.4 dw 563 ;0.6 dw 1536 ;0.8 dw 2048 ;1.0 dw 0 ;1.2 dw -6144 ;1.4 dw -8192 ;1.6 dw -9216 ;1.8 dw -10240 ;2.0 dw -10240 ;2.2 dw -10240 ;2.4 dw -10240 ;2.6 dw -10240 ;2.8 dw -10240 ;3.0 dw -10240 ;3.2 TOKEN_END ;Integer mach table on Cmq ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cmq due to mach TOKEN_BEGIN AIR_CM_Q dw 0 ;0.0 dw -1229 ;0.2 dw -2458 ;0.4 dw -3686 ;0.6 dw -5222 ;0.8 dw -6758 ;1.0 dw -5068 ;1.2 dw -3379 ;1.4 dw -1690 ;1.6 dw 0 ;1.8 dw 1024 ;2.0 dw 2048 ;2.2 dw 2048 ;2.4 dw 2048 ;2.6 dw 2048 ;2.8 dw 2048 ;3.0 dw 2048 ;3.2 TOKEN_END ;Integer mach table on Cmih ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cmih due to mach TOKEN_BEGIN AIR_CM_IH dw 0 ;0.0 dw 102 ;0.2 dw 205 ;0.4 dw 410 ;0.6 dw 1024 ;0.8 dw 717 ;1.0 dw 717 ;1.2 dw 717 ;1.4 dw 717 ;1.6 dw 717 ;1.8 dw 717 ;2.0 dw 717 ;2.2 dw 717 ;2.4 dw 717 ;2.6 dw 717 ;2.8 dw 717 ;3.0 dw 717 ;3.2 TOKEN_END ;Integer mach table on Cm0 ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cm0 due to mach TOKEN_BEGIN AIR_CMO dw 0 ;0.0 dw 0 ;0.2 dw 0 ;0.4 dw 2 ;0.6 dw 6 ;0.8 dw 6 ;1.0 dw 6 ;1.2 dw 6 ;1.4 dw 6 ;1.6 dw 6 ;1.8 dw 6 ;2.0 dw 6 ;2.2 dw 6 ;2.4 dw 6 ;2.6 dw 6 ;2.8 dw 6 ;3.0 dw 6 ;3.2 TOKEN_END ;Integer mach table on Cyb ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cyb due to mach TOKEN_BEGIN AIR_CY_BETA dw 0 ;0.0 dw 0 ;0.2 dw 0 ;0.4 dw 0 ;0.6 dw 0 ;0.8 dw 0 ;1.0 dw 0 ;1.2 dw 0 ;1.4 dw 0 ;1.6 dw 0 ;1.8 dw 0 ;2.0 dw 0 ;2.2 dw 0 ;2.4 dw 0 ;2.6 dw 0 ;2.8 dw 0 ;3.0 dw 0 ;3.2 TOKEN_END ;Integer mach table on Cydr ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cydr due to mach TOKEN_BEGIN AIR_CY_DELTAR dw 0 ;0.0 dw 0 ;0.2 dw 0 ;0.4 dw 0 ;0.6 dw -10 ;0.8 dw -10 ;1.0 dw -10 ;1.2 dw -10 ;1.4 dw -10 ;1.6 dw -10 ;1.8 dw -10 ;2.0 dw -10 ;2.2 dw -10 ;2.4 dw -10 ;2.6 dw -10 ;2.8 dw -10 ;3.0 dw -10 ;3.2 TOKEN_END ;Integer mach table on Cyr ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cyr due to mach TOKEN_BEGIN AIR_CY_R dw 0 ;0.0 dw 0 ;0.2 dw 0 ;0.4 dw 0 ;0.6 dw 0 ;0.8 dw 0 ;1.0 dw 0 ;1.2 dw 0 ;1.4 dw 0 ;1.6 dw 0 ;1.8 dw 0 ;2.0 dw 0 ;2.2 dw 0 ;2.4 dw 0 ;2.6 dw 0 ;2.8 dw 0 ;3.0 dw 0 ;3.2 TOKEN_END ;Integer mach table on Cyp ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cyp due to mach TOKEN_BEGIN AIR_CY_P dw 0 ;0.0 dw 0 ;0.2 dw 0 ;0.4 dw 0 ;0.6 dw 0 ;0.8 dw 0 ;1.0 dw 0 ;1.2 dw 0 ;1.4 dw 0 ;1.6 dw 0 ;1.8 dw 0 ;2.0 dw 0 ;2.2 dw 0 ;2.4 dw 0 ;2.6 dw 0 ;2.8 dw 0 ;3.0 dw 0 ;3.2 TOKEN_END ;Integer mach table on Clb ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Clb due to mach TOKEN_BEGIN AIR_CL_BETA dw 0 ;0.0 dw 0 ;0.2 dw 0 ;0.4 dw 0 ;0.6 dw 0 ;0.8 dw 0 ;1.0 dw 0 ;1.2 dw 0 ;1.4 dw 0 ;1.6 dw 0 ;1.8 dw 0 ;2.0 dw 0 ;2.2 dw 0 ;2.4 dw 0 ;2.6 dw 0 ;2.8 dw 0 ;3.0 dw 0 ;3.2 TOKEN_END ;Integer mach table on Cldr ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cldr due to mach TOKEN_BEGIN AIR_CL_DELTAR dw 0 ;0.0 dw 0 ;0.2 dw 0 ;0.4 dw 0 ;0.6 dw 0 ;0.8 dw 0 ;1.0 dw 0 ;1.2 dw 0 ;1.4 dw 0 ;1.6 dw 0 ;1.8 dw 0 ;2.0 dw 0 ;2.2 dw 0 ;2.4 dw 0 ;2.6 dw 0 ;2.8 dw 0 ;3.0 dw 0 ;3.2 TOKEN_END ;Integer mach table on Clda ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Clda due to mach TOKEN_BEGIN AIR_CL_DELTAA dw 0 ;0.0 dw 0 ;0.2 dw -10 ;0.4 dw -21 ;0.6 dw -41 ;0.8 dw -51 ;1.0 dw -51 ;1.2 dw -51 ;1.4 dw -51 ;1.6 dw -51 ;1.8 dw -51 ;2.0 dw -51 ;2.2 dw -51 ;2.4 dw -51 ;2.6 dw -51 ;2.8 dw -51 ;3.0 dw -51 ;3.2 TOKEN_END ;Integer mach table on Clr ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Clr due to mach TOKEN_BEGIN AIR_CL_R dw 0 ;0.0 dw 0 ;0.2 dw 0 ;0.4 dw 0 ;0.6 dw 0 ;0.8 dw 0 ;1.0 dw 0 ;1.2 dw 0 ;1.4 dw 0 ;1.6 dw 0 ;1.8 dw 0 ;2.0 dw 0 ;2.2 dw 0 ;2.4 dw 0 ;2.6 dw 0 ;2.8 dw 0 ;3.0 dw 0 ;3.2 TOKEN_END ;Integer mach table on Clp ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Clp due to mach TOKEN_BEGIN AIR_CL_P dw 0 ;0.0 dw -10 ;0.2 dw -41 ;0.4 dw -102 ;0.6 dw -205 ;0.8 dw -225 ;1.0 dw -225 ;1.2 dw -225 ;1.4 dw -225 ;1.6 dw -225 ;1.8 dw -225 ;2.0 dw -225 ;2.2 dw -225 ;2.4 dw -225 ;2.6 dw -225 ;2.8 dw -225 ;3.0 dw -225 ;3.2 TOKEN_END ;Integer mach table on Cnb ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cnb due to mach TOKEN_BEGIN AIR_CN_BETA dw 0 ;0.0 dw 0 ;0.2 dw 0 ;0.4 dw 0 ;0.6 dw 0 ;0.8 dw 0 ;1.0 dw 0 ;1.2 dw 0 ;1.4 dw 0 ;1.6 dw 0 ;1.8 dw 0 ;2.0 dw 0 ;2.2 dw 0 ;2.4 dw 0 ;2.6 dw 0 ;2.8 dw 0 ;3.0 dw 0 ;3.2 TOKEN_END ;Integer mach table on Cndr ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cndr due to mach TOKEN_BEGIN AIR_CN_DELTAR dw 0 ;0.0 dw 0 ;0.2 dw 0 ;0.4 dw 0 ;0.6 dw 0 ;0.8 dw 0 ;1.0 dw 0 ;1.2 dw 0 ;1.4 dw 0 ;1.6 dw 0 ;1.8 dw 0 ;2.0 dw 0 ;2.2 dw 0 ;2.4 dw 0 ;2.6 dw 0 ;2.8 dw 0 ;3.0 dw 0 ;3.2 TOKEN_END ;Integer mach table on Cnda ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cnda due to mach TOKEN_BEGIN AIR_CN_DELTAA dw 0 ;0.0 dw 0 ;0.2 dw -2 ;0.4 dw -4 ;0.6 dw -6 ;0.8 dw -6 ;1.0 dw -6 ;1.2 dw -6 ;1.4 dw -6 ;1.6 dw -6 ;1.8 dw -6 ;2.0 dw -6 ;2.2 dw -6 ;2.4 dw -6 ;2.6 dw -6 ;2.8 dw -6 ;3.0 dw -6 ;3.2 TOKEN_END ;Integer mach table on Cnr ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cnr due to mach TOKEN_BEGIN AIR_CN_R dw 0 ;0.0 - dw 0 ;0.2 dw 0 ;0.4 dw 0 ;0.6 dw 0 ;0.8 dw 0 ;1.0 dw 0 ;1.2 dw 0 ;1.4 dw 0 ;1.6 dw 0 ;1.8 dw 0 ;2.0 dw 0 ;2.2 dw 0 ;2.4 dw 0 ;2.6 dw 0 ;2.8 dw 0 ;3.0 dw 0 ;3.2 TOKEN_END ;Integer mach table on Cnp ;IN: Mach index (see Guidlines on Mach Integer Tables) ;OUT: Delta Cnp due to mach TOKEN_BEGIN AIR_CN_P dw 0 ;0.0 dw 0 ;0.2 dw 0 ;0.4 dw 0 ;0.6 dw 0 ;0.8 dw 0 ;1.0 dw 0 ;1.2 dw 0 ;1.4 dw 0 ;1.6 dw 0 ;1.8 dw 0 ;2.0 dw 0 ;2.2 dw 0 ;2.4 dw 0 ;2.6 dw 0 ;2.8 dw 0 ;3.0 dw 0 ;3.2 TOKEN_END ;**** END OF MACH TABLES ********************************* ;***END OF AERODYNAMICS********************************************************************************************** ;******************************************************************************************************************** ;******************************************************************************************************************** ;****START OF ENGINE DATA ******************************************************************************************* ;Commanded N2 (corrected) vs. Throttle table at 0 Mach (max 9 rows, 11 columns) ;NOTE: The specific (low) Mach value is specified at the 0,0 position of the table ; This table is used in conjunction with the AIR_70_MACH_HI_CORRECTED_COMMANDED_NE table ;IN: X: 1/atmospheric press ratio (Psl/P)(note: use inverse of delta pressure ratio so that values are in increasing order) ;IN: Y: %Power Lever / Throttle ;OUT: Corrected N2 for MACH = 0 TOKEN_BEGIN AIR_70_MACH_0_CORRECTED_COMMANDED_NE UINT32 9,3 ; %PL 0' 70K' REAL8 0.00, 1.00 , 22.57 ; Pressure Ratio (Psl/P) REAL8 0.00, 66.00, 82.50 REAL8 0.42, 78.80, 95.40 REAL8 0.51, 82.50, 98.50 REAL8 0.61, 87.40, 101.10 REAL8 0.70, 92.00, 103.10 REAL8 0.79, 96.20, 105.70 REAL8 0.93, 103.10, 108.06 REAL8 1.00, 105.00, 108.06 TOKEN_END ;Commanded N2 (corrected) vs. Throttle table at HI Mach (max 9 rows, 11 columns) ;NOTE: The specific (HI) Mach value is specified at the 0,0 position of the table ; This table is used in conjunction with the AIR_70_MACH_0_CORRECTED_COMMANDED_NE table ;IN: X: 1/atmospheric press ratio (Psl/P)(note: use inverse of delta pressure ratio so that values are in increasing order) ;IN: Y: %Power Lever / Throttle ;OUT: Corrected N2 for specified MACH TOKEN_BEGIN AIR_70_MACH_HI_CORRECTED_COMMANDED_NE UINT32 9,3 ; %PL 0' 70K' REAL8 0.90, 1.00 , 22.57 ; Pressure Ratio (Psl/P) REAL8 0.00, 62.00, 82.50 REAL8 0.42, 77.00, 95.40 REAL8 0.51, 80.20, 98.50 REAL8 0.61, 84.80, 101.10 REAL8 0.70, 89.10, 103.10 REAL8 0.79, 92.20, 105.70 REAL8 0.93, 96.00, 108.06 REAL8 1.00, 98.20, 108.06 TOKEN_END ;N2 (Corrected) vs. FuelFlow constant ; where the constant is a normalized ratio of actual fuelflow parameter to static thrust ;IN: Normalized Fuelflow constant ;OUT: N2 (corrected) TOKEN_BEGIN AIR_70_CORRECTED_N2_FROM_FF UINT32 10 REAL8 0.00000, 0.0 REAL8 0.00294, 10.0 REAL8 0.01180, 30.0 REAL8 0.02066, 40.0 REAL8 0.03397, 50.0 REAL8 0.05317, 60.0 REAL8 0.13391, 80.0 REAL8 0.25771, 90.0 REAL8 0.54000, 100.0 REAL8 0.68686, 105.0 TOKEN_END ;N1 vs N2 & Mach lookup table (max 13 rows, 11 columns) ;IN: X: Mach ;IN: Y: N2 (corrected) ;OUT: N1 (corrected) TOKEN_BEGIN AIR_70_N2_TO_N1_TABLE UINT32 13,3 ;rows,cols ;N2 REAL8 0.0, 0.0, 0.9 ; Mach REAL8 0.0, 0.0, 0.0 REAL8 10.0, 2.0, 12.0 REAL8 20.0, 7.0, 22.5 REAL8 30.0, 10.2, 32.0 REAL8 40.0, 15.1, 41.2 REAL8 50.0, 20.1, 47.0 REAL8 60.0, 28.0, 52.5 REAL8 70.0, 38.0, 57.0 REAL8 80.0, 50.0, 67.5 REAL8 90.0, 70.0, 80.8 REAL8 100.0, 89.4, 100.8 REAL8 110.0, 112.0, 120.0 TOKEN_END ;N1 vs Thrust table (max 21 rows, 11 columns) ;IN: X: Mach ;IN: Y: N1 (corrected) ;OUT: Gross Thurst (corrected) / static thrust TOKEN_BEGIN AIR_70_N1_AND_MACH_ON_THRUST UINT32 21,3 ;ROWS,COLS ; N1 REAL8 0.0, 0.0, 0.9 ; Mach REAL8 0.0, 0.00000, 0.00000 REAL8 20.0, 0.02540, 0.07409 REAL8 25.0, 0.05080, 0.15929 REAL8 30.0, 0.07983, 0.25563 REAL8 35.0, 0.11249, 0.34829 REAL8 40.0, 0.20000, 0.44457 REAL8 45.0, 0.28100, 0.54086 REAL8 50.0, 0.36800, 0.70600 REAL8 55.0, 0.44500, 0.84400 REAL8 60.0, 0.52100, 0.99700 REAL8 65.0, 0.62900, 1.15500 REAL8 70.0, 0.72600, 1.32400 REAL8 75.0, 0.81800, 1.57500 REAL8 80.0, 0.90000, 1.77400 REAL8 85.0, 0.99200, 1.95300 REAL8 90.0, 1.04300, 2.05500 REAL8 95.0, 1.06900, 2.15700 REAL8 100.0, 1.12500, 2.24400 REAL8 105.0, 1.14500, 2.27500 REAL8 110.0, 1.17000, 2.31600 TOKEN_END ;N1 vs AirFlow/Ram Drag (max 21 rows, 11 columns) ;IN: X: Mach ;IN: Y: N1 (corrected) ;OUT: Normalized Airflow (Corrected) = Airflow / inlet area TOKEN_BEGIN AIR_70_CORRECTED_AIRFLOW UINT32 21,3 ; N1 REAL8 0.0, 0.0, 0.9 ; Mach REAL8 0.0, 0.00000, 0.00000 REAL8 20.0, 4.28954, 14.08090 REAL8 25.0, 6.06131, 15.15328 REAL8 30.0, 7.80977, 16.31892 REAL8 35.0, 9.58154, 17.50787 REAL8 40.0, 11.32999, 18.62688 REAL8 45.0, 13.14839, 19.79252 REAL8 50.0, 14.87353, 20.91153 REAL8 55.0, 16.62198, 21.98391 REAL8 60.0, 18.39375, 23.14955 REAL8 65.0, 20.02564, 24.22194 REAL8 70.0, 21.84404, 25.34095 REAL8 75.0, 23.66243, 26.39002 REAL8 80.0, 25.62070, 27.76547 REAL8 85.0, 27.83541, 29.16424 REAL8 90.0, 30.25994, 30.58632 REAL8 95.0, 32.12496, 32.00839 REAL8 100.0, 33.59366, 33.17403 REAL8 105.0, 34.71267, 34.12985 REAL8 110.0, 35.29549, 35.22555 TOKEN_END ;Afterburner on thrust table (max 10 entries) ;IN: Mach ;OUT: Scalar on Thrust for max afterburner. ; Output is scaled by percent afterburner active TOKEN_BEGIN AIR_70_AFTERBURNER_ON_THRUST_TABLE UINT32 6 ;Entries REAL8 0.0, 1.58 REAL8 0.4, 1.69 REAL8 0.8, 1.80 REAL8 1.2, 1.84 REAL8 1.6, 1.85 REAL8 2.0, 1.85 TOKEN_END ;Dynamic primary exhaust nozzle available flag TOKEN_BEGIN AIR_70_PRIMARY_NOZZLE BOOL FALSE ;fVariablePrimaryNozzle TOKEN_END ;Nozzle animation table and afterburner offset (if primary nozzle available) ; The output is the percent open of the primary nozzle (max 1.0) TOKEN_BEGIN AIR_10XPACK_N1_MACH_ON_NOZZLE FLOAT32 0.30 ;Offset due to afterburner state ;Exhaust nozzle table (max 4 rows, 3 columns) ;IN: X: mach, ;IN: Y: Corrected N1 ;OUT: Primary Nozzle Pct open UINT32 4,3 ;ROWS,COLS ;N1 M-lo M-hi REAL8 0.00, 0.80, 1.05 REAL8 40.00, 0.55, 0.80 REAL8 65.00, 0.62, 0.85 REAL8 96.00, 0.70, 0.90 TOKEN_END ;Thrust reverser flags TOKEN_BEGIN AIR_70_REVERSER_NOZZLE BOOL TRUE ;fReverserNozzle BOOL FALSE ;fMachControlledReverserNozzle TOKEN_END ;Engine Pressure Ratio TOKEN_BEGIN AIR_70_EPR REAL8 1.0 ;EPR tuning constant REAL8 1.4 ;Max EPR REAL8 14.0 ;EPR time constant TOKEN_END ;Oil Temperature TOKEN_BEGIN AIR_61S_OIL_TEMPERATURE REAL8 1.000000 ; Oil temp tuning constant REAL8 0.000000 ; Oil temp cooling constant REAL8 600.000000 ; Max Oil Temp (deg Rankine) REAL8 0.010000 ; Oil temp time constant TOKEN_END ;Oil Pressure TOKEN_BEGIN AIR_61S_OIL_PRESSURE REAL8 1.000000 ; Oil pressure tuning constant REAL8 19440.000000 ; Oil pressure max (PSF) REAL8 0.800000 ; Oil pressure time constant TOKEN_END ;Interstage turbine temperature TOKEN_BEGIN AIR_70_ITT REAL8 1.0 ;ITT tuning constant REAL8 2400.0 ;ITT peak temperature REAL8 2.0 ;ITT time constant TOKEN_END ;Exhaust Gas Temperature TOKEN_BEGIN AIR_61S_EGT REAL8 1.000000 ; EGT tuning constant REAL8 1285.000000 ; EGT peak temperature (typical peak: 1200 degF + 460) REAL8 2.000000 ; EGT time constant TOKEN_END ;**** PID CONTROLLERS ******************************************************* ;The following PID controllers are utilized only by computer controlled (AI) aircraft system for heading and airspeed control TOKEN_BEGIN AIR_AP_PID_CONTROLLERSF AIRFILE_PID <0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000> ; UNUSED AIRFILE_PID <1.8, 0.0, 0.0, 1.5, 2.0, 0.0, 20.0> ; head_hold pid_p, i, i2, d, i_boundary, i2_boundary, d_boundary AIRFILE_PID <0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000> ; UNUSED AIRFILE_PID <0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000> ; UNUSED AIRFILE_PID <0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000> ; UNUSED AIRFILE_PID <0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000> ; UNUSED AIRFILE_PID <0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000> ; UNUSED AIRFILE_PID <0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000> ; UNUSED AIRFILE_PID <0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000> ; UNUSED AIRFILE_PID <0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000> ; UNUSED AIRFILE_PID <0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000> ; UNUSED AIRFILE_PID <0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000> ; UNUSED AIRFILE_PID <0.35, 0.002, 0.0, 8.5, 10.0, 0.0, 80.0> ; airspeed_hold pid_p, i, i2, d, i_boundary, i2_boundary, d_boundary AIRFILE_PID <0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000> ; UNUSED AIRFILE_PID <0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000> ; UNUSED TOKEN_END sim_size equ $ - sim_data end |
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