Path: ACPro/ACProAerodynamics
% Computes the lift and drag coefficients for a swept wing
Type LDDeltaWing for a demo of the Space Shuttle wing.
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Form:
[cD, cL, kI, y] = LDDeltaWing( v, h, d )
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Inputs
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v (1,:) Velocity (m/s)
h (1,:) Altitude (m)
d (1,1) Aircraft parameters
.length (1,:) Representative length (e.g. mean chord) (m)
.oswaldEff (1,1) Oswald efficiency factor (0.9 to 1.0)
.aspectRatio (1,1) Aspect ratio for wing (length/mean chord)
.thickness (1,1) Ratio of length to thickness
.s (1,1) Area
.zetaTrans (1,1) Damping for transonic
.sweep (1,:) Sweep angles (deg)
.span (1,:) Span of each section
alpha (1,1) Angle of attack (rad)
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Outputs
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cD (1,:) Drag coefficient
cL (1,:) Lift coefficient
kI (1,:) Induced drag coefficient
y (1,:) Lift and drag data structure
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See also LiftAndDrag.
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ACPro: ACProAerodynamics/CDSkinFriction ACPro: ACProAerodynamics/DragCoeff ACPro: ACProAerodynamics/FormDragCoeff ACPro: ACProAerodynamics/InducedDragCoeff ACPro: ACProAerodynamics/LiftAndDrag ACPro: ACProAerodynamics/LiftCoeff ACPro: ACProAerodynamics/PrandtlGlauertCorrection AerospaceUtils: AeroData/AtmData Common: Atmosphere/StdAtm Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Analysis/Logistic Math: Trigonometry/CosD
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