Shock Losses - GasTurb

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Shock Losses

Shock losses are of interest for supersonic aircraft intakes, for example. In an interactive picture you can play with upstream Mach Number and Shock Angle. The static pressure ratio Ps2/Ps1 and the total pressure ratio P2/P1 are shown as bars on the right side of the picture. Note that all calculations are done employing a constant isentropic coefficient.

 
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