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Path: ACPro/ACProAerodynamics
% Compute force and torque an aircraft from M = 0 to M = inf.
Since version 4 (ACT).
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Form:
[force, torque, cL, cD] = AeroForceAndTorqueCombined( alpha, beta,
V, e, u, d, display )
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Inputs
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alpha (1,:) Angle of attack
beta (1,:) Sideslip
V (1,:) Velocity
e (.) Environment data structure
.a (1,:) Speed of sound
.rho (1,:) Density
.kV (1,:) Kinematic viscosity
.t (1,:) Time vector
u (n,:) Control angle vector. Mapping is in d
d (.) Data structure
.g (.) Aircraft CAD data structure for
Newtonian Flow
.surface
.name (1,:) Name of surface
.logistic
.m (1,1) Mach number for center
.a (1,1) Coefficient
.b (1,1) Coefficient
display (1,1) If 1 display the active surfaces
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Outputs
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force (3,1) Force in body frame (N)
torque (3,1) Torque in body frame (Nm)
cL (1,:) Lift coefficient
cD (1,:) Drag coefficient
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See also NewtonianAerodynamicsFromCAD, InducedDragCoeff
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AC: ACCoord/UFromAlphaBeta ACPro: ACProAerodynamics/ConcordeLD ACPro: ACProAerodynamics/InducedDragCoeff ACPro: ACProData/FlatPlateAircraft ACPro: Newtonian/NewtonianAerodynamicsFromCAD Common: Atmosphere/StdAtm Common: Graphics/Plot2D Common: Graphics/TimeLabl Math: Linear/Cross Math: Linear/Unit
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