LiftAndDragCoeff:
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Lift and drag coefficients for an airfoil.
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Form:
[cL, cD] = LiftAndDragCoeff( d, alpha )
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Inputs
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d (1,1) Data structure
.cLAlpha (1,1) Lift curve slope
.rho (1,1) Air density (kg/m^3)
.u0 (1,1) Speed (m/s)
.c (1,1) Chord (m)
.s (1,1) Span (m)
.e (1,1) Oswald efficency factor
.mu (1,1) Viscosity
alpha (1,:) Angle of attack (rad)
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Outputs
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cL (1,1) Lift coefficient
cD (1,1) Drag coefficient
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Reference: R. Miller. 16.751 Course Notes. M.I.T. Department of
Aeronautics and Astronautics, 1977.
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Children:
Common: Graphics/Plot2D
