LiftAndDragCoeff:

--------------------------------------------------------------------------
   Lift and drag coefficients for an airfoil.
--------------------------------------------------------------------------
   Form:
   [cL, cD] = LiftAndDragCoeff( d, alpha )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   d          (1,1)  Data structure
                     .cLAlpha    (1,1)  Lift curve slope
                     .rho        (1,1)  Air density (kg/m^3)
                     .u0         (1,1)  Speed (m/s)
                     .c          (1,1)  Chord (m)
                     .s          (1,1)  Span (m)
                     .e          (1,1)  Oswald efficency factor
                     .mu         (1,1)  Viscosity
   alpha      (1,:)  Angle of attack (rad)

   -------
   Outputs
   -------
   cL         (1,1)  Lift coefficient
   cD         (1,1)  Drag coefficient

--------------------------------------------------------------------------
   Reference: R. Miller. 16.751 Course Notes. M.I.T. Department of
              Aeronautics and Astronautics, 1977. 
--------------------------------------------------------------------------

Children:

Common: Graphics/Plot2D