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Path: ACPro/ACProAerodynamics
-------------------------------------------------------------------------- Computes the drag polar, cD = cD0 + k*cL^2 This is the simplest realistic drag model for an aircraft. Since version 5. -------------------------------------------------------------------------- Form: cD = DragPolar( cD0, cL, kI ) -------------------------------------------------------------------------- ------ Inputs ------ cD0 (1,:) Zero lift drag coefficient cL (1,:) Lift coefficient kI (1,:) Induced drag coefficient ------- Outputs ------- cD (1,:) Drag coefficient -------------------------------------------------------------------------- Reference: John D. Anderson, Jr. "Introduction to Flight", 3rd Edition, McGraw-Hill, 1989 --------------------------------------------------------------------------
Common: Graphics/Plot2D
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