Sample: PistonSample.asm
| ; Copyright (c) Microsoft Corporation. All rights reserved. ; Sample Piston Engine Airplane 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 1.2 ; CL flaps REAL8 0.000000 ; UNUSED REAL8 0.715988 ; CLih REAL8 -0.273018 ; CLde REAL8 0.000000 ; UNUSED TOKEN_END TOKEN_BEGIN AIR_80_DRAG_PARAMS REAL8 0.065 ; CDo REAL8 0.07 ; CD flaps REAL8 0.007000 ; CD gear REAL8 0.000000 ; CD spoiler TOKEN_END TOKEN_BEGIN AIR_80_PITCH_PARAMS REAL8 2.133893 ; CMih REAL8 -1.6 ; CMde REAL8 -0.051200 ; CMde due to propwash REAL8 -2.601277 ; CLq REAL8 0.988016 ; CL adot REAL8 2.0 ; CM adot REAL8 -28.770823 ; CMq REAL8 -10.000000 ; CMq due to propwash REAL8 0.0 ; CMo REAL8 -0.07 ; CM flap REAL8 -1.066947 ; CM delta trim REAL8 0.020000 ; CM gear REAL8 0.000000 ; CM spoiler TOKEN_END TOKEN_BEGIN AIR_80_SIDE_FORCE_PARAMS REAL8 -0.569647 ; CyB REAL8 0.038363 ; CyP REAL8 0.018805 ; CyR REAL8 -0.153025 ; Cy Delta Rudder TOKEN_END TOKEN_BEGIN AIR_80_ROLL_PARAMS REAL8 0.045 ; ClB REAL8 -0.9 ; ClP REAL8 -0.061076 ; ClR REAL8 0.000000 ; Cl Delta Spoiler REAL8 -0.269225 ; Cl Delta Aileron REAL8 0.010 ; Cl Delta Rudder TOKEN_END TOKEN_BEGIN AIR_80_YAW_PARAMS REAL8 0.099757 ; CnB REAL8 0.034553 ; CnP REAL8 -0.524805 ; CnR REAL8 -3.000000 ; CnR due to propwash REAL8 0.000000 ; UNUSED REAL8 0.000000 ; UNUSED REAL8 -0.002345 ; Cn Delta Aileron REAL8 0.063277 ; Cn Delta Rudder REAL8 0.002048 ; 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 -0.366, -1.528 REAL8 -0.078, 0.000 REAL8 0.017, 0.590 REAL8 0.262, 2.096 REAL8 0.288, 2.183 REAL8 0.314, 2.096 REAL8 0.340, 1.528 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 -0.550, -0.545 REAL8 -0.375, -0.545 REAL8 -0.305, -0.273 REAL8 -0.288, -0.227 REAL8 -0.271, -0.189 REAL8 0.000, 0.000 REAL8 0.271, 0.189 REAL8 0.288, 0.227 REAL8 0.305, 0.273 REAL8 0.375, 0.545 REAL8 0.550, 0.545 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 0.000000 ; aileron_trim_scale REAL8 0.314159 ; rudder_trim_scale TOKEN_END ;Elevator effectiveness scaling table (max 7 entries) ; IN: Elevator angle (radians) ; OUT: Effectiveness scalar TOKEN_BEGIN AIR_ELEVATOR_SCALING dd 7 ; Number of Entries REAL8 -0.349000, 1.000000 ; REAL8 -0.262000, 0.800000 ; REAL8 -0.175000, 0.700000 ; REAL8 0.000000, 0.500000 ; REAL8 0.175000, 0.700000 ; REAL8 0.349000, 0.800000 ; REAL8 0.524000, 1.000000 ; TOKEN_END ;Aileron effectiveness scaling table (max 7 entries) ; IN: Aileron angle (radians) ; OUT: Effectiveness scalar TOKEN_BEGIN AIR_AILERON_SCALING dd 7 ; Number of Entries REAL8 -0.209000, 1.000000 ; REAL8 -0.140000, 0.800000 ; REAL8 -0.070000, 0.600000 ; REAL8 0.000000, 0.400000 ; REAL8 0.105000, 0.600000 ; REAL8 0.209000, 0.800000 ; REAL8 0.279000, 1.000000 ; TOKEN_END ;Rudder effectiveness scaling table (max 7 entries) ; IN: Rudder angle (radians) ; OUT: Effectiveness scalar TOKEN_BEGIN AIR_RUDDER_SCALING dd 7 ; Number of Entries REAL8 -0.489000, 1.000000 ; REAL8 -0.349000, 0.800000 ; REAL8 -0.175000, 0.600000 ; REAL8 0.000000, 0.400000 ; REAL8 0.175000, 0.600000 ; REAL8 0.349000, 0.800000 ; REAL8 0.489000, 1.000000 ; 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 dd 5 ; Number of Entries REAL8 0.000000, 1.000000 ; REAL8 135.000000, 1.000000 ; REAL8 300.000000, 0.800000 ; REAL8 500.000000, 0.500000 ; REAL8 700.000000, 0.200000 ; 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 dd 5 ; Number of Entries REAL8 0.000000, 1.000000 ; REAL8 135.000000, 0.800000 ; REAL8 300.000000, 0.500000 ; REAL8 500.000000, 0.200000 ; REAL8 700.000000, 0.100000 ; 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 dd 5 ; Number of Entries REAL8 0.000000, 1.000000 ; REAL8 300.000000, 0.500000 ; REAL8 600.000000, 0.200000 ; REAL8 1482.000000, 0.000000 ; REAL8 1500.000000, -0.100000 ; 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 dd 5 ; Number of Entries REAL8 0.000000, 1.000000 ; REAL8 300.000000, 1.000000 ; REAL8 800.000000, 0.500000 ; REAL8 1000.000000, 0.300000 ; REAL8 1500.000000, 0.200000 ; 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, 1.000000 ; REAL8 3.000000, 1.000000 ; REAL8 4.000000, 0.800000 ; REAL8 6.000000, 0.650000 ; REAL8 8.000000, 0.200000 ; 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 dd 7 ; Number of Entries REAL8 -17.000000, 0.020000 ; REAL8 -13.000000, 0.010000 ; REAL8 -10.000000, 0.000000 ; REAL8 16.000000, 0.000000 ; REAL8 17.000000, -0.005000 ; REAL8 18.000000, 0.012000 ; REAL8 19.000000, 0.020000 ; 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 dd 7 ; Number of Entries REAL8 -16.000000, 0.020000 ; REAL8 -13.000000, 0.015000 ; REAL8 -10.000000, 0.000000 ; REAL8 16.000000, 0.000000 ; REAL8 17.000000, -0.007000 ; REAL8 18.000000, 0.006000 ; REAL8 19.000000, 0.016000 ; 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, 0.800000 ; REAL8 0.000000, 1.000000 ; REAL8 8.000000, 1.000000 ; REAL8 15.000000, 0.400000 ; REAL8 20.000000, 0.200000 ; 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, 0.000000 ; REAL8 0.000000, 1.000000 ; REAL8 13.000000, 0.300000 ; REAL8 15.000000, 0.000000 ; 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, 0.200000 ; REAL8 -15.000000, 0.100000 ; REAL8 -10.000000, 0.600000 ; REAL8 0.000000, 1.000000 ; REAL8 10.000000, 0.600000 ; REAL8 15.000000, 0.100000 ; REAL8 90.000000, 0.200000 ; 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 -180.000000, 1.000000 ; REAL8 -90.000000, 0.500000 ; REAL8 -15.000000, 0.100000 ; REAL8 -10.000000, 0.400000 ; REAL8 0.000000, 1.000000 ; REAL8 10.000000, 0.400000 ; REAL8 15.000000, 0.100000 ; REAL8 90.000000, 0.500000 ; REAL8 180.000000, 1.000000 ; 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 -180.000000, 1.000000 ; REAL8 -90.000000, 0.500000 ; REAL8 -15.000000, 0.100000 ; REAL8 -10.000000, 0.600000 ; REAL8 0.000000, 1.000000 ; REAL8 10.000000, 0.600000 ; REAL8 15.000000, 0.100000 ; REAL8 90.000000, 0.500000 ; REAL8 180.000000, 1.000000 ; 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 -180.000000, 1.000000 ; REAL8 -90.000000, 0.400000 ; REAL8 -15.000000, 0.100000 ; REAL8 -10.000000, 0.600000 ; REAL8 0.000000, 1.000000 ; REAL8 10.000000, 0.600000 ; REAL8 15.000000, 0.100000 ; REAL8 90.000000, 0.400000 ; REAL8 180.000000, 1.000000 ; 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 dd 17 ; Number of Entries REAL8 0.000000, 1.000000 ; REAL8 0.200000, 1.000000 ; REAL8 0.400000, 1.000000 ; REAL8 0.600000, 1.000000 ; REAL8 0.800000, 1.000000 ; REAL8 1.000000, 1.000000 ; REAL8 1.200000, 1.000000 ; REAL8 1.400000, 1.000000 ; REAL8 1.600000, 1.000000 ; REAL8 1.800000, 1.000000 ; REAL8 2.000000, 1.000000 ; REAL8 2.200000, 1.000000 ; REAL8 2.400000, 1.000000 ; REAL8 2.600000, 1.000000 ; REAL8 2.800000, 1.000000 ; REAL8 3.000000, 1.000000 ; REAL8 3.200000, 1.000000 ; 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 ; Mach = 0.0 CL_DELTAE dw 0 ; Mach = 0.2 table output scale => 1.0 = 2048 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CL_ADOT dw 0 ; Mach = 0.2 table output scale => 1.0 = 2048 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CL_Q dw 0 ; Mach = 0.2 table output scale => 1.0 = 2048 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CL_IH dw 0 ; Mach = 0.2 table output scale => 1.0 = 2048 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CM_DELTAE dw 0 ; Mach = 0.2 table output scale => 1.0 = 2048 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CM_ALPHADOT dw 0 ; Mach = 0.2 table output scale => 1.0 = 2048 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CM_Q dw 0 ; Mach = 0.2 table output scale => 1.0 = 2048 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CM_IH dw 0 ; Mach = 0.2 table output scale => 1.0 = 2048 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CM0 dw 0 ; Mach = 0.2 dw 8 ; Mach = 0.4 dw 45 ; Mach = 0.6 dw 150 ; Mach = 0.8 dw 240 ; Mach = 1.0 dw 50 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CY_BETA dw 0 ; Mach = 0.2 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CY_DELTAR dw 0 ; Mach = 0.2 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CY_R dw 0 ; Mach = 0.2 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CY_P dw 0 ; Mach = 0.2 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CL_BETA dw 0 ; Mach = 0.2 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CL_DELTAR dw 0 ; Mach = 0.2 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CL_DELTAA dw 0 ; Mach = 0.2 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CL_R dw 0 ; Mach = 0.2 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CL_P dw 0 ; Mach = 0.2 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CN_BETA dw 0 ; Mach = 0.2 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CN_DELTAR dw 0 ; Mach = 0.2 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CN_DELTAA dw 0 ; Mach = 0.2 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 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 ; Mach = 0.0 CN_R dw 0 ; Mach = 0.2 dw 1000 ; Mach = 0.4 dw 5000 ; Mach = 0.6 dw 6000 ; Mach = 0.8 dw 7000 ; Mach = 1.0 dw 6000 ; Mach = 1.2 dw 3000 ; Mach = 1.4 dw 3000 ; Mach = 1.6 dw 3000 ; Mach = 1.8 dw 3000 ; Mach = 2.0 dw 3000 ; Mach = 2.2 dw 3000 ; Mach = 2.4 dw 3000 ; Mach = 2.6 dw 3000 ; Mach = 2.8 dw 3000 ; Mach = 3.0 dw 3000 ; Mach = 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 ; Mach = 0.0 CN_P dw 0 ; Mach = 0.2 dw 0 ; Mach = 0.4 dw 0 ; Mach = 0.6 dw 0 ; Mach = 0.8 dw 0 ; Mach = 1.0 dw 0 ; Mach = 1.2 dw 0 ; Mach = 1.4 dw 0 ; Mach = 1.6 dw 0 ; Mach = 1.8 dw 0 ; Mach = 2.0 dw 0 ; Mach = 2.2 dw 0 ; Mach = 2.4 dw 0 ; Mach = 2.6 dw 0 ; Mach = 2.8 dw 0 ; Mach = 3.0 dw 0 ; Mach = 3.2 TOKEN_END ;**** END OF MACH TABLES ********************************* ;***END OF AERODYNAMICS********************************************************************************************** ;******************************************************************************************************************** ;******************************************************************************************************************** ;****START OF ENGINE DATA ******************************************************************************************* ;Piston engine mechanical efficiency table (max 5 entries) ;IN: RPM ;OUT: Power Efficiency scalar TOKEN_BEGIN AIR_61S_ENG_MECHANICAL_EFFICIENCY dd 5 ; Number of Entries REAL8 400.000000, 0.9000 ; REAL8 750.000000, 0.67200 ; REAL8 1725.000000, 0.672000 ; REAL8 1840.000000, 0.640000 ; REAL8 2300.000000, 0.640000 ; TOKEN_END ;Piston engine friction table (max 4 entries) ;IN: RPM ;OUT: Torque due to Friction applied in resistance to RPM (ft-lbs) TOKEN_BEGIN AIR_61S_ENGINE_FRICTION dd 4 ; Number of Entries REAL8 -300.000000, -41.00 ; REAL8 300.000000, 41.00 ; REAL8 900.000000, 40.00 ; REAL8 2300.000000, 95.0 ; TOKEN_END ;**ENGINE TEMPERATURE AND PRESSURE CONSTANTS ;Exhaust Gas Temperature TOKEN_BEGIN AIR_61S_EGT REAL8 1.000000 ; EGT tuning constant REAL8 1660.000000 ; EGT peak temperature (typical peak: 1200 degF + 460) REAL8 2.000000 ; EGT tc TOKEN_END ;Cylinder Head Temperature TOKEN_BEGIN AIR_61S_CHT REAL8 1.000000 ; CHT tuning constant REAL8 0.650000 ; CHT cooling constant REAL8 960.000000 ; CHT Max Temp (deg Rankine) REAL8 0.015000 ; CHT tc TOKEN_END ;Oil Temperature TOKEN_BEGIN AIR_61S_OIL_TEMPERATURE REAL8 1.000000 ; Oil temp tuning constant REAL8 0.210000 ; Oil temp cooling constant REAL8 660.000000 ; Max Oil Temp (deg Rankine) REAL8 0.030000 ; Oil temp tc TOKEN_END ;Oil Pressure TOKEN_BEGIN AIR_61S_OIL_PRESSURE REAL8 1.000000 ; Oil pressure tuning constant REAL8 10800.000000 ; Oil pressure max (PSF) REAL8 0.800000 ; Oil pressure tc TOKEN_END ;Fuel Pressure TOKEN_BEGIN AIR_61S_FUEL_PRESSURE REAL8 1.000000 ; Fuel pressure tuning constant REAL8 720.000000 ; Fuel pressure max (PSF) REAL8 2.000000 ; Fuel pressure tc TOKEN_END ;Radiator Temperature TOKEN_BEGIN AIR_61S_RADIATOR_TEMPERATURE REAL8 1.000000 ; Radiator temp tuning constant REAL8 0.015000 ; Radiator temp cooling constant REAL8 670.000000 ; Radiator temp max (deg Rankine) REAL8 0.020000 ; Radiator temp tc 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 7,13 ;rows,cols ;-------------------- REAL8 0.0, 0.00, 0.20, 0.40, 0.60, 0.80, 1.00, 1.20, 1.40, 1.60, 1.80, 2.00, 2.20 REAL8 15.0, 0.15, 0.40, 0.71, 0.86, 0.72, 0.50, 0.34, 0.23, 0.15, 0.11, 0.08, 0.06 REAL8 20.0, 0.10, 0.30, 0.62, 0.79, 0.86, 0.80, 0.55, 0.42, 0.30, 0.19, 0.12, 0.09 REAL8 25.0, 0.08, 0.23, 0.49, 0.72, 0.82, 0.87, 0.82, 0.60, 0.41, 0.28, 0.18, 0.13 REAL8 30.0, 0.07, 0.18, 0.33, 0.50, 0.72, 0.82, 0.87, 0.85, 0.56, 0.42, 0.26, 0.19 REAL8 35.0, 0.06, 0.16, 0.26, 0.40, 0.55, 0.72, 0.82, 0.86, 0.87, 0.70, 0.40, 0.30 REAL8 40.0, 0.05, 0.12, 0.23, 0.33, 0.45, 0.57, 0.70, 0.81, 0.86, 0.87, 0.85, 0.50 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 7,14 ;rows,cols ;-------------------- REAL8 0.0, 0.000, 0.200, 0.400, 0.600, 0.800, 1.000, 1.200, 1.400, 1.600, 1.800, 2.000, 2.200, 2.400 REAL8 15.0, 0.025, 0.025, 0.025, 0.022, 0.009, -0.057, -0.188, -0.338, -0.522, -0.705, -0.915, -1.092, -1.220 REAL8 20.0, 0.062, 0.052, 0.049, 0.042, 0.037, 0.010, -0.074, -0.188, -0.338, -0.525, -0.726, -0.942, -1.120 REAL8 25.0, 0.098, 0.094, 0.088, 0.080, 0.070, 0.050, 0.020, -0.040, -0.134, -0.272, -0.468, -0.717, -0.933 REAL8 30.0, 0.138, 0.132, 0.128, 0.120, 0.110, 0.099, 0.078, 0.040, -0.017, -0.110, -0.248, -0.468, -0.741 REAL8 35.0, 0.206, 0.198, 0.188, 0.178, 0.163, 0.150, 0.130, 0.105, 0.070, 0.023, -0.074, -0.254, -0.510 REAL8 40.0, 0.250, 0.242, 0.233, 0.223, 0.214, 0.204, 0.190, 0.175, 0.150, 0.118, 0.072, 0.019, -0.059 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 <2.000000, 0.000000, 0.000000, 0.000763, 2.000000, 0.000000, 20.000000> ; 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 <2.400000, 0.000840, 0.000000, 10.00000, 50.00000, 0.000000, 50.00000> ; 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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