Path: ACPro/ACProAerodynamics
% Lift and moment coefficients of a thin wing.
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Form:
CLCMWing( alpha, z )
[cL, cM] = CLCMWing( alpha, z )
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Inputs
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alpha (1,:) Angle of attack (rad)
z (1,:) Camber ratio z = 1/8R where R is the radius of
curvature
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Inputs
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cL (1,:) Lift coefficent
cM (1,:) Quarter chord moment coefficient
cL0 (1,:) Lift coefficent at zero angle of attack
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Reference: McCormick, B. W., "Aerodynamics, Aeronautics and Flight
Mechanics," Wiley, 1979, p. 86.
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