LDDeltaWing:

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
   ------
   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)

   -------
   Outputs
   -------
   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.
--------------------------------------------------------------------------

Children:

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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