Sample: TurbineHeloSampleType2.asm
TurbineHeloSampleType2.asm |
| ; Copyright (c) Microsoft Corporation. All rights reserved. ; Sample Turbine Helicopter Flight Dynamics File ; ; Sample Turbine Engine Helicopter Dynamics File (Secondary Type) ; ; 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 TOKEN_BEGIN AIR_HELI_VERTICAL_TAIL FLOAT64 8.08 ; vertical tail cross sectional area, ft**2 FLOAT64 5.19 ; vertical tail aspect ratio, dimensionless FLOAT64 0.0349 ; vertical tail cant angle, radians FLOAT64 229.6 ; vertical tail longitudinal position, inches FLOAT64 3.35 ; vertical tail WL position, assumed 1/2 span, inches FLOAT64 0.2 ; lift at zero angle of attack, CLo, nondim FLOAT64 0.004 ; horizontal tail drag at zero alpha FLOAT64 1.0 ; vertical effectiveness factor due to rotor wash TOKEN_END TOKEN_BEGIN AIR_HELI_HORIZONTAL_TAIL FLOAT64 9.65 ; horizontal tail cross sectional area, ft**2 FLOAT64 4.29 ; horizontal tail aspect ratio, dimensionless FLOAT64 0.0 ; radians, horizontal tail angle from vertical axis, assumed FLOAT64 146.2 ; horizontal tail longitudinal position, inches FLOAT64 1.0 ; horiz vertical position, approximate, inches REAL8 -0.35 ; lift at zero angle of attack, CLo, nondim FLOAT64 0.004 ; horizontal tail drag at zero alpha FLOAT64 0.75 ; Horiz effectiveness factor due to rotor wash TOKEN_END TOKEN_BEGIN AIR_HELI_MAIN_ROTOR FLOAT64 0.0 ; (lat) main rotor is centered over center line REAL8 -4.0 ; (long) inches, main rotor fuselage station FLOAT64 57.6 ; (vert) inches, measured from 3 view from water line 00 station REAL8 -0.01745 ; rads mr lat tilt, 1. degrees to left, actual slightly higher REAL8 -0.01745 ; rads mr long tilt, 1 degrees forward, actual slightly higher FLOAT64 16.625 ; main rotor radius FLOAT64 1.08 ; main rotor blade chord length in feet FLOAT64 2.0 ; Number blades in Main Rotor FLOAT64 267.75 ; rotational mass moment of inertia, .333*m*r^2 FLOAT64 0.75 ; rotor hub loss factor FLOAT64 2.5 ; main rotor section lift coefficient, per radian FLOAT64 0.009 ; section drag coefficient, the bucket value FLOAT64 0.0413 ; Main solidity ratio, dimensionless - Nc/pi*R FLOAT64 868.31 ; Main rotor area FLOAT64 15.11 ; Main rotor aspect ratio, dimensionless FLOAT64 41.36 ; rad/sec, equates to 395 rpm for the main rotors TOKEN_END TOKEN_BEGIN AIR_HELI_TAIL_ROTOR FLOAT64 24.0 ; (lat) inches, measured from 3 view from water line 00 station FLOAT64 229.6 ; (long) inches, tail rotor lateral REAL8 -8.0 ; (vert) inches, tail rotor fuselage station, inches FLOAT64 0.0 ; radians. tail rotor lateral tilt, assumed FLOAT64 0.0 ; radians. tail rotor longitudinal tilt, assumed FLOAT64 5.4167 ; tail rotor radius FLOAT64 0.5 ; tail rotor blade chord length in feet FLOAT64 2.0 ; Number blades in Tail Rotor FLOAT64 1.004 ; estimated FLOAT64 0.60 ; tail hub loss factor FLOAT64 4.3 ; tail rotor section lift coefficient FLOAT64 0.009 ; section drag coefficient, the bucket value FLOAT64 0.1177 ; tail solidity ratio, dimensionless - Nc/pi*R TOKEN_END TOKEN_BEGIN AIR_HELI_MISCELLANOUS FLOAT64 29.01 ; (front_area) fuselage frontal cross sectional area, ft**2 FLOAT64 88.16 ; (side_area ) fuselage side cross sectional area, ft**2 FLOAT64 64.03 ; (plane_area) fuselage top plane cross sectional area, ft**2 FLOAT64 0.4 ; (F_fuse_Cd) Front face fuselage drag coefficient (assumed) FLOAT64 1.8 ; (S_fuse_Cd) Side face fuselage drag coefficient (assumed) FLOAT64 0.27 ; (P_fuse_Cd) Plane face fuselage drag coefficient TOKEN_END sim_size equ $ - sim_data end |
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