CDCLSubsonic:

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
--------------------------------------------------------------------------

Children:

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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