Path: ACPro/ACProAerodynamics
% Lift coefficient for subsonic, supersonic and hypersonic flight.
This combines subsonic, supersonic and hypersonic. All regimes have a
Mach number correction. If alpha is not entered it will compute just
the lift curve coefficient.
Type CLComposite for a demo.
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Form:
cL = CLComposite( m, d, alpha, gamma )
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Inputs
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m (1,:) Freestream Mach number
d (.) Data structure
.cLM1 (1,1) Lift ratio at Mach 1
.cLAlpha (1,1) Lift curve slope (1/rad)
.sweep (1,1) Sweep angle (rad)
.thicknessRatio (1,1) Thickness to chord ratio
alpha (1,:) Angle of attack (rad)
gamma (1,1) Ratio of specific heats (Default = 1.4)
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Outputs
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cL (1,:) Lift coefficient
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See also CPHypersonic
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AC: Aero/RayleighPitotTube ACPro: ACProAerodynamics/CPHypersonic AerospaceUtils: AeroData/AtmData AerospaceUtils: AtmosphericCalculations/AtmGamma Common: Atmosphere/StdAtm Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
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