Question: Supersonic Inlet Performance: The figure below shows a two - dimensional diffuser that produces no net turning of the flow. For the geometry shown, calculate

Supersonic Inlet Performance: The figure below shows a two-dimensional diffuser that produces no net turning of the flow. For the geometry shown, calculate the overall stagnation pressure ratio for a flight Mach number of M=3.5. Neglect all losses except those occurring in the shocks.
Supersonic Inlet Performance: The figure below

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