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Path: ACPro/ACProAerodynamics
% Lift and drag coefficients for subsonic, supersonic and hypersonic flight.
This combines subsonic, supersonic and hypersonic. All regimes
have a Mach number correction.
Since version 2014.1
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Form:
[cL, cD, cD0] = CDCLComposite( m, d, alpha, p )
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Inputs
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m (1,:) Freestream Mach number
d (.) Data structure
.oswaldEff (1,1) Oswald efficiency factor
.aspectRatio (1,1) Aspect ratio
.cLM1 (1,1) Lift ratio at Mach 1
.cLAlpha (1,1) Lift curve slope (1/rad)
.sweep (1,1) Sweep angle (rad)
.l (1,1) Characteristic length (m)
.u (1,:) Velocity (m/s)
.nu (1,1) Kinematic viscosity
.cDM1 (1,1) Drag coefficient at Mach 1
.mDD (1,1) Drag divergence Mach number
.thicknessRatio (1,1) Thickness to chord ratio
alpha (1,:) Angle of attack (rad)
p (.) Standard atmosphere data structure
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Outputs
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cL (1,:) Lift coefficient
cD (1,:) Drag coefficient
cD0 (1,:) Zero lift drag coefficient
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See also CLComposite, CD0Composite
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ACPro: ACProAerodynamics/CD0Composite ACPro: ACProAerodynamics/CLComposite ACPro: ACProAerodynamics/ConcordeLD ACPro: ACProAerodynamics/LiftToDragFromMach AerospaceUtils: AtmosphericCalculations/AtmGamma Common: Atmosphere/StdAtm Common: Graphics/Plot2D
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