InletLoss:

Path: ACPro/ACEngine

% Computes the inlet loss in an aircraft engine due to shockwaves.

 Computes p02/p01 due to inlet shock losses. Uses an empirical 
 relationship. The ratio will be 1 for Mach numbers between 0 and 1. Above
 Mach 7.812 the ratio is zero.

 Type InletLoss for a demo.
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   Form:
    pR = InletLoss( m )
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   ------
   Inputs
   ------
   m   (1,:)   Mach number

   -------
   Outputs
   -------
   pR (1,:)    p02/p01

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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:

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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