TotalPressureAndTemperature:

Path: ACPro/ACEngine

% Computes the total pressure and temperature at a Mach number.
 Computes the total pressure and temperature given a pressure and 
 temperature of a gas flow at Mach number m.

 Type TotalPressureAndTemperature for a demo at 10 km altitude.
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   Form:
   [p0, t0] = TotalPressureAndTemperature( p, t, gamma, m )
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   ------
   Inputs
   ------
   p       (1,1)   Pressure
   t       (1,1)   Temperature
   gamma   (1,1)   Ratio of specific heats
   m       (1,:)   Mach number

   -------
   Outputs
   -------
   p0      (1,:)   Total pressure
   t0      (1,:)   Total temperature

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   Reference:  Benson, T. J., "An Interactive Educational Tool for 
               Turbojet Engines," May 1995, NASA Lewis Research Center
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Children:

AerospaceUtils: AeroData/AtmData
AerospaceUtils: AtmosphericCalculations/AtmGamma
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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