Path: ACPro/ACProAerodynamics
% Induced drag coefficient for all Mach numbers. At supersonic speeds provides combined vortex and wave drag. Drag is cD0 + k*cL^2. This function includes a linear term in the square root for the supersonic mach numbers that allows it to match the subsonic induced drag at M = 1. Otherwise it would produce a jump in the drag at M = 1. Type InducedDragCoeff for a demo -------------------------------------------------------------------------- Form: k = InducedDragCoeff( e, aR, m ) -------------------------------------------------------------------------- ------ Inputs ------ e (1,1) Oswald efficiency factor (0 to 1) aR (1,1) Wing aspect ratio m (1,:) Mach number ------- Outputs ------- k (1,:) Induced drag coefficient -------------------------------------------------------------------------- Reference: http://adg.stanford.edu/aa241/drag/LiftWaveDrag.html --------------------------------------------------------------------------
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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