Sample: TurboPropSample.asm
TurboPropSample.asm |
| ; Copyright (c) Microsoft Corporation. All rights reserved. ; Sample Turbo Prop 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 0.000000 ; CL spoiler REAL8 0.673300 ; CL flaps REAL8 0.000000 ; UNUSED REAL8 -0.94800 ; CLih REAL8 -0.38900 ; CLde REAL8 0.000000 ; UNUSED TOKEN_END TOKEN_BEGIN AIR_80_DRAG_PARAMS REAL8 0.023 ; CDo REAL8 0.080000 ; CD flaps REAL8 0.017000 ; CD gear REAL8 0.000000 ; CD spoiler TOKEN_END TOKEN_BEGIN AIR_80_PITCH_PARAMS REAL8 -3.21631 ; CMih REAL8 -1.46480 ; CMde REAL8 0.000000 ; CMde due to propwash REAL8 -7.81250 ; CLq REAL8 4.327600 ; CL adot REAL8 9.765600 ; CM adot REAL8 -35.1560 ; CMq REAL8 0.000000 ; CMq due to propwash REAL8 -0.02930 ; CMo REAL8 -0.10000 ; CM flap REAL8 -0.70000 ; CM delta trim REAL8 0.000000 ; CM gear REAL8 0.000000 ; CM spoiler TOKEN_END TOKEN_BEGIN AIR_80_SIDE_FORCE_PARAMS REAL8 -0.57226 ; CyB REAL8 0.000000 ; CyP REAL8 0.346190 ; CyR REAL8 -0.09131 ; Cy Delta Rudder TOKEN_END TOKEN_BEGIN AIR_80_ROLL_PARAMS REAL8 0.0976000 ; ClB REAL8 -1.465000 ; ClP REAL8 -0.146480 ; ClR REAL8 0.0000000 ; Cl Delta Spoiler REAL8 -0.200200 ; Cl Delta Aileron REAL8 0.0151360 ; Cl Delta Rudder TOKEN_END TOKEN_BEGIN AIR_80_YAW_PARAMS REAL8 0.146480 ; CnB REAL8 0.063476 ; CnP REAL8 -0.97650 ; CnR REAL8 0.000000 ; CnR due to propwash REAL8 0.000000 ; UNUSED REAL8 0.000000 ; UNUSED REAL8 -0.03027 ; Cn Delta Aileron REAL8 0.050290 ; 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 UINT32 13 ;NUMBER OF ENTRIES REAL8 -3.142, 0.000 REAL8 -2.356, 0.500 REAL8 -1.571, 0.000 REAL8 -0.308, -1.085 REAL8 -0.029, 0.000 REAL8 0.000, 0.159 REAL8 0.244, 1.488 REAL8 0.279, 1.550 REAL8 0.314, 1.488 REAL8 0.349, 1.085 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 UINT32 13 ;NUMBER OF ENTRIES REAL8 -3.142, 0.000 REAL8 -0.541, -0.603 REAL8 -0.367, -0.603 REAL8 -0.297, -0.302 REAL8 -0.279, -0.251 REAL8 -0.262, -0.209 REAL8 0.000, 0.000 REAL8 0.262, 0.209 REAL8 0.279, 0.251 REAL8 0.297, 0.302 REAL8 0.367, 0.603 REAL8 0.541, 0.603 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 5 ;NUMBER OF ENTRIES REAL8 -0.349, 1.0 ;-20 DEG REAL8 -0.175, 1.0 ;-10 DEG REAL8 0.0, 1.0 ; 0 REAL8 0.175, 1.0 ;10 DEG REAL8 0.349, 1.0 ;20 DEG TOKEN_END 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, 0.5 ;-45 DEG REAL8 -0.524, 0.6 ;-30 DEG REAL8 -0.175, 0.9 ;-10 DEG REAL8 0.0, 1.0 REAL8 0.175, 0.9 ;10 DEG REAL8 0.524, 0.6 ;30 DEG REAL8 0.785, 0.5 ;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, 0.6 ;Ve = 543 keas REAL8 1500.0, 0.5 ;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, 0.8 ;Ve = 297 keas REAL8 800.0, 0.2 ;Ve = 485 keas REAL8 1000.0, 0.2 ;Ve = 543 keas REAL8 1500.0, 0.2 ;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, 0.7 ;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 -25.0, 1.0 REAL8 -12.0, 1.0 REAL8 12.0, 1.0 REAL8 16.0, 1.0 REAL8 25.0, 1.0 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 -15.0, 1.0 REAL8 0.0, 1.0 REAL8 13.0, 1.0 REAL8 14.0, 1.0 REAL8 25.0, 1.0 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 -15.0, 1.0 REAL8 0.0, 1.0 REAL8 5.0, 1.0 REAL8 16.0, 1.0 REAL8 25.0, 1.0 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 -15.0, 1.0 REAL8 0.0, 1.0 REAL8 11.0, 1.0 REAL8 16.0, 0.7 REAL8 25.0, 0.7 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 -15.0, 1.0 REAL8 0.0, 1.0 REAL8 13.0, 1.0 REAL8 16.0, 1.0 REAL8 25.0, 1.0 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 -15.0, 1.0 REAL8 0.0, 1.0 REAL8 13.0, 1.0 REAL8 16.0, 1.0 REAL8 25.0, 1.0 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 -180.0, 1.0 REAL8 -90.0, 0.2 REAL8 -16.0, 0.2 REAL8 -10.0, 0.8 REAL8 0.0, 1.0 REAL8 10.0, 0.8 REAL8 16.0, 0.2 REAL8 90.0, 0.2 REAL8 180.0, 1.0 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 -16.0, 0.2 REAL8 -10.0, 0.6 REAL8 0.0, 1.0 REAL8 10.0, 0.6 REAL8 16.0, 0.2 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 -16.0, 0.2 REAL8 -10.0, 0.3 REAL8 0.0, 1.0 REAL8 10.0, 0.3 REAL8 16.0, 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 -16.0, 0.2 REAL8 -10.0, 0.4 REAL8 0.0, 1.0 REAL8 10.0, 0.4 REAL8 16.0, 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 0 ;0.2 dw 0 ;0.4 dw -33 ;0.6 dw -99 ;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 ******************************************************************************************* ;Turboprop Commanded N1 (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 N1 for MACH = 0 TOKEN_BEGIN AIR_70_MACH_0_CORRECTED_COMMANDED_NE UINT32 9,3 ; ;SSL 35K REAL8 0.0, 1.0, 4.237 ; Pressure Ratio (Psl/P) REAL8 0.00, 62.00, 67.02 REAL8 0.42, 80.80, 94.48 REAL8 0.51, 86.20, 101.52 REAL8 0.61, 89.70, 108.06 REAL8 0.75, 95.70, 108.06 REAL8 0.80, 97.00, 108.06 REAL8 0.90, 99.60, 108.06 REAL8 1.00, 101.50, 108.06 TOKEN_END ;Turboprop Commanded N1 (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 N1 for specified MACH TOKEN_BEGIN AIR_70_MACH_HI_CORRECTED_COMMANDED_NE UINT32 9,3 ; ;SSL 35K REAL8 0.9, 1.0, 4.237 REAL8 0.00, 44.29, 60.46 REAL8 0.42, 63.39, 75.10 REAL8 0.51, 68.28, 79.40 REAL8 0.61, 73.18, 83.80 REAL8 0.70, 76.61, 88.00 REAL8 0.79, 80.12, 90.00 REAL8 0.93, 82.38, 94.00 REAL8 1.00, 83.83, 95.00 TOKEN_END ;N1 to Shaft Torque table (max 3 elements) ;IN: N1 (corrected) ;OUT: Percent maximum torque (corrected) TOKEN_BEGIN AIR_70_N1_TO_SHAFT_TORQUE UINT32 3 ;Pct Max Trq REAL8 0.0, 0.0 REAL8 40.0, 0.031 REAL8 101.5, 1.9 TOKEN_END ;Atmospheric density on shaft torque (max 10 entries)) ;IN: Ambient density (slug/ft^3) ;OUT: Scalar on corrected shaft torque TOKEN_BEGIN AIR_80_DENSITY_ON_TP_TORQUE UINT32 10 REAL8 0.000225, 0.000 ;60k feet REAL8 0.000587, 0.800 ;40k feet REAL8 0.000739, 0.830 ;35k feet REAL8 0.000891, 0.890 ;30k feet REAL8 0.001144, 0.930 ;25k feet REAL8 0.001268, 0.970 ;20k feet REAL8 0.001496, 1.000 ;15k feet REAL8 0.001756, 1.025 ;10k feet REAL8 0.002049, 1.050 ;5k feet REAL8 0.002377, 1.000 ;0k feet TOKEN_END ;Engine RPM vs. Friction Torque table (max 4 entries) ;IN: Percent engine RPM ;OUT: Torque due to Friction expressed as a percentage of max torque TOKEN_BEGIN AIR_61S_ENGINE_FRICTION UINT32 4 REAL8 -10.0,-0.2 REAL8 10.0, 0.2 REAL8 70.0, 0.8 REAL8 100.0, 0.8 TOKEN_END ;N1 vs Thrust table (max 21 rows, 11 columns) ; NOTE: While generally insignificant with turboprops, ; exhaust thrust can be modeled here ;IN: X: Mach ;IN: Y: N1 (corrected) ;OUT: Gross Thurst (corrected) / static thrust TOKEN_BEGIN AIR_70_N1_AND_MACH_ON_THRUST UINT32 3,3 ;ROWS,COLS ; N1 REAL8 0.0, 0.0, 0.9 ; Mach REAL8 0.0, 0.00000, 0.00000 REAL8 100.0, 0.00000, 0.00000 TOKEN_END ;N1 vs AirFlow/Ram Drag (max 21 rows, 11 columns) ; NOTE: While generally insignificant with turboprops, ; intake ram can be modeled here ;IN: X: Mach ;IN: Y: N1 (corrected) ;OUT: Normalized Airflow (Corrected) = Airflow / inlet area TOKEN_BEGIN AIR_70_CORRECTED_AIRFLOW UINT32 3,3 ; N1 REAL8 0.0, 0.0, 0.9 ; Mach REAL8 0.0, 0.00000, 0.00000 REAL8 100.0, 0.00000, 0.00000 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 0.8 ;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 ;*****END ENGINE DATA ********************************************************* ;*****START PROPELLER DATA **************************************************** ;Propeller efficiency 2D input table (max 12 x 14 entries) ;relates engine power input to thrust produced by prop ; ;First row is propeller advance ratio ;First column is propeller blade angle ; ;IN: Y: Blade Angle (degrees) ;IN: X: Advance Ratio,J where J = Vel (Ft/sec) / (Diameter (Ft) * Rev/Sec) ;OUT: Efficiency, where Thrust = (EngPower / Vel) * Efficiency TOKEN_BEGIN AIR_61S_PROP_EFFICIENCY UINT32 12,13 ;rows,cols ;-------------------- REAL8 0.0 , 0.0 , 0.2 , 0.4 , 0.6 , 0.8 , 1.0 , 1.2 , 1.4 , 1.6 , 1.8 , 2.0 , 2.2 REAL8 10.0, 0.000, 0.021, 0.046, 0.155, 0.619, 0.700, 0.598, 0.456, 0.400, 0.343, 0.271, 0.215 REAL8 15.0, 0.380, 0.542, 0.670, 0.790, 0.500, 0.403, 0.360, 0.320, 0.290, 0.253, 0.210, 0.164 REAL8 20.0, 0.081, 0.280, 0.560, 0.760, 0.860, 0.625, 0.552, 0.498, 0.425, 0.361, 0.307, 0.255 REAL8 25.0, 0.050, 0.200, 0.425, 0.650, 0.800, 0.883, 0.750, 0.674, 0.595, 0.509, 0.425, 0.332 REAL8 30.0, 0.040, 0.160, 0.325, 0.505, 0.680, 0.820, 0.890, 0.870, 0.748, 0.636, 0.542, 0.449 REAL8 35.0, 0.030, 0.130, 0.270, 0.400, 0.550, 0.690, 0.810, 0.885, 0.909, 0.700, 0.606, 0.523 REAL8 40.0, 0.020, 0.100, 0.210, 0.330, 0.440, 0.560, 0.690, 0.790, 0.865, 0.904, 0.900, 0.712 REAL8 45.0, 0.010, 0.109, 0.179, 0.269, 0.371, 0.478, 0.573, 0.660, 0.760, 0.831, 0.881, 0.906 REAL8 50.0, 0.000, 0.081, 0.155, 0.240, 0.313, 0.397, 0.471, 0.552, 0.629, 0.720, 0.785, 0.840 REAL8 55.0, 0.000, 0.067, 0.135, 0.206, 0.283, 0.353, 0.427, 0.506, 0.571, 0.640, 0.710, 0.743 REAL8 70.0, 0.000, 0.000, 0.000, 0.000, 0.000, 0.000, 0.000, 0.000, 0.000, 0.000, 0.000, 0.000 TOKEN_END ;Propeller Power Required Coefficient (max 12 x 14 entries) ;Relates propeller speed and angle and aircraft speed to power required to turn the propeller ; ;First row is propeller advance ratio ;First column is propeller blade angle ; ;IN: Y: Blade Angle (degrees) ;IN: X: Advance Ratio,J where J = Vel (Ft/sec) / (Diameter (Ft) * Rev/Sec) ;OUT: Power Required Coefficient, Cp TOKEN_BEGIN AIR_61S_PROP_PWR_CF UINT32 12,14 ;rows,cols ;-------------------- REAL8 0.0, 0.0000, 0.2000, 0.4000, 0.6000, 0.8000, 1.0000, 1.2000, 1.4000, 1.6000, 1.8000, 2.00 , 2.2000, 2.4000 REAL8 10.0, 0.0600, 0.0450, 0.0250, -0.0600, -0.2360, -0.7500, -1.5800, -2.6000, -3.5700, -4.8200, -6.0500, -7.1700, -8.3900 REAL8 15.0, 0.1200, 0.0950, 0.0700, 0.0350, -0.0500, -0.3780, -1.0800, -1.7800, -2.6100, -3.4500, -4.3900, -5.4500, -6.6000 REAL8 20.0, 0.2480, 0.2250, 0.1800, 0.1420, 0.0890, -0.0320, -0.2500, -0.8060, -1.6300, -2.3900, -3.2000, -4.0600, -5.0000 REAL8 25.0, 0.3540, 0.3430, 0.3090, 0.2630, 0.2220, 0.1460, 0.0000, -0.1670, -0.5670, -1.2600, -2.0200, -2.9400, -3.7800 REAL8 30.0, 0.4720, 0.4680, 0.4610, 0.4300, 0.3920, 0.3470, 0.2900, 0.1650, 0.0000, -0.3560, -0.7600, -1.3500, -2.2800 REAL8 35.0, 0.6050, 0.6080, 0.5860, 0.5590, 0.5550, 0.5360, 0.5060, 0.4610, 0.4040, 0.3050, 0.1270, -0.2340, -1.6300 REAL8 40.0, 0.7680, 0.7530, 0.7370, 0.7220, 0.7220, 0.7000, 0.6770, 0.6540, 0.6120, 0.5590, 0.4830, 0.3850, 0.0770 REAL8 45.0, 0.9120, 0.9080, 0.8890, 0.8890, 0.8890, 0.8890, 0.8930, 0.8780, 0.8510, 0.8100, 0.7340, 0.6500, 0.5290 REAL8 50.0, 1.0300, 1.0300, 1.0300, 1.0300, 1.0300, 1.0300, 1.0300, 1.0300, 1.0070, 0.9610, 0.9000, 0.8170, 0.6840 REAL8 55.0, 1.1170, 1.1170, 1.1170, 1.1170, 1.1170, 1.1170, 1.1170, 1.1170, 1.1170, 1.1170, 1.1170, 1.1170, 1.1170 REAL8 60.0, 1.2610, 1.2610, 1.2610, 1.2610, 1.2610, 1.2610, 1.2610, 1.2610, 1.2610, 1.2610, 1.2610, 1.2610, 1.2610 TOKEN_END ;*****END PROPELLER DATA **************************************************** ;**** 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, 7.0, 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 TOKEN_END sim_size equ $ - sim_data end |
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