Question: Consider a supersonic inlet consisting of two oblique shocks followed by a normal shock before entering the internal subsonic diffuser. Suppose the flight Mach

Consider a supersonic inlet consisting of two oblique shocks followed by a normal shock before entering the 

Consider a supersonic inlet consisting of two oblique shocks followed by a normal shock before entering the internal subsonic diffuser. Suppose the flight Mach number is 2.5, the first turning angle is 0,= 10 while the second turning is an additional 10 (so that it is a total of 20 relative to the freestream). Assume that there are no other external losses while the internal subsonic diffuser loss is 3%. Determine the total pressure ratio at this flight Mach number of 2.5. Note that a subsonic diffuser loss of 3% means that P Po 0.97. Hint: when the problem asks for the total pressure loss, simply multiple your solution for Pa/Poa by 0.97 in order to obtain P/Poa Normal shock

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