Path: ACPro/ACProAerodynamics
% Computes the drag polar
Computes the drag polar, cD = cD0 + k*cL^2
This is the simplest realistic drag model for an aircraft.
Type DragPolar for a demo.
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Form:
cD = DragPolar( cD0, cL, kI )
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Inputs
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cD0 (1,:) Zero lift drag coefficient
cL (1,:) Lift coefficient
kI (1,:) Induced drag coefficient
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Outputs
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cD (1,:) Drag coefficient
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Reference: John D. Anderson, Jr. "Introduction to Flight",
3rd Edition, McGraw-Hill, 1989
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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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