AOverAStar:

Path: ACPro/ACEngine

% A/A* computation from mach number and ratio of specific heats.
--------------------------------------------------------------------------
   Form:
   a = AOverAStar( gamma, machNo )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   gamma      (1,1)   Ratio of specific heats
   machNo     (1,:)   Mach number

   -------
   Outputs
   -------
   a          (1,:)   A/A*

--------------------------------------------------------------------------
   Reference: Mattingly, "Elements of Gas Turbine Propulsion,"
              McGraw-Hill, 1996, p. 878.
--------------------------------------------------------------------------

Children:

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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