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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
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m (1,:) Mach number
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Outputs
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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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Common: Graphics/Plot2D
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