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Path: ACPro/Newtonian
% Compute force and torque for a CAD model.
Shadowing is not modeled. Vertices must be entered into faces
counterclockwise. The axis of rotation for the fuselage should be
[0;0;0]; Plots will be against whichever input, alpha or beta, changes
the most.
Lift and drag are assumed to be in the x-z plane. Drag is opposite
the velocity vector. Lift is normal to drag in the x-z plane.
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Form:
[force, torque, cL, cD, lOverD, aTotal] = NewtonianAerodynamicsFromCAD( alpha, beta, uMag,
rho, g, c, angle, uSurf, display )
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Inputs
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alpha (1,:) Angle of attack (rad)
beta (1,:) Sideslip angle (rad)
uMag (1,:) Velocity (m/s)
rho (1,:) Density (kg/m^3)
g (.) CAD data structure
c (3,1) Center of mass (m)
angle (n,:) Surface angles (rad)
uSurf (3,n) Axis of rotation for the surface
display (1,1) If entered draw the vehicle and active surfaces
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Outputs
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force (3,:) Force (N)
torque (3,:) Torque (Nm)
cL (1,:) Lift coefficient
cD (1,:) Drag coefficient
lOverD (1,:) L/D
aTotal (1,1) Total area
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Reference for Demo: X-15 Flight 91, http://en.wikipedia.org/wiki/X-15_Flight_91
http://www.whiteeagleaerospace.com/blog/2009/08/24/the-highest-x-15-flight/
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