A supersonic diffuser is designed to operate at a freestream Mach number of 1.7. Determine the ratio of mass flow rate through the diffuser when it operates at a freestream Mach number of 2 with a normal shock in front (see Fig. 6.9) to that at the design condition. Assume M=1 at the throat for both cases. Also assume that the freestream static conditions remain the same. What is the ratio of the capture area to the throat area in each case?

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Free stream (a) Capture streamtube Throat Free stream (b) Throat Fig. 6.9 Illustration of a supersonic diffuser at a design and b off-design operating condition