Path: ACPro/ACProAerodynamics
% Subsonic lift and drag coefficients for a flat plate. The default Standard Atmosphere is at 1000 m. Default e is 0.95 and default aR is 6. Type CDCLSubsonic for a demo. One demo shows the variation of cD and cL with respect to Mach. The other shows the variation with respect to angle of attack. -------------------------------------------------------------------------- Form: [cD, cL] = CDCLSubsonic( m, alpha, p, l, aR, e, cLAlpha ) -------------------------------------------------------------------------- ------ Inputs ------ m (1,:) Freestream Mach number alpha (1,:) Angle of attack (rad) p (.) Standard atmosphere data structure l (1,1) Characteristic length e (1,1) Oswald efficiency factor (0 to 1) aR (1,1) Wing aspect ratio cLAlpha (1,:) Either a constant or a function handle ------- Outputs ------- cD (1,:) Drag coefficient cL (1,:) Lift coefficient -------------------------------------------------------------------------- See also CDSkinFriction, InducedDragCoeff, DragPolar --------------------------------------------------------------------------
ACPro: ACProAerodynamics/CDSkinFriction ACPro: ACProAerodynamics/DragPolar ACPro: ACProAerodynamics/InducedDragCoeff 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
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