ClimbAngle:

Path: ACPro/ACPerformance

% Compute climb angle

   Ground effect is included and the scale factor is the square root of s.
   This uses DragCoeff for the drag coefficients. If the altitude is zero
   then the gravity force is assumed to be zero.

   Type ClimbAngle for a demo
   Since version 5.
--------------------------------------------------------------------------
   Form:
   gamma = ClimbAngle( h, v, d )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   h               (1,:) Altitude (m)
   v               (1,:) Velocity (m/s)
   d                (.)  Data structure
                         .mass         (1,1) Mass (kg)
                         .s            (1,1) Reference area (m^2)
                         .cLAlpha      (1,1) Lift coefficient
                         .thrust       (1,:) Thrust force (N)
                         .length       (1,1) Representative length (e.g. mean chord) (m)
                         .oswaldEff    (1,1) Oswald efficiency factor (optional)
                         .aspectRatio	(1,1) Aspect ratio for wing (length/mean chord)
                         .thickness    (1,1) Ratio of length to thickness
                         .m1Peak       (1,1) Peak at M = 1 an alternative to zetaTrans
   -------
   Outputs
   -------
   gamma          (1,:) Climb angle

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   See also DragCoeff
--------------------------------------------------------------------------

Children:

ACPro: ACProAerodynamics/DragCoeff
Common: Atmosphere/StdAtm
Common: Database/Constant
Common: Graphics/Plot2D

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