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Problem 4 (25 pts). Consider a simple model scramjet engine shown below consisting of an inlet followed by a combustor. At cruise, the inlet is designed to provide a wave free (no shock, no expansion fan) flow into the combustor. The forebody of the inlet can be treated as a wedge with a turning angle of α=10^∘. This inlet is designed such that it compresses the incoming flow using exactly two finite strength oblique shock waves (i.e., Mach waves are not considered as oblique shock waves). Note

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SOLVED:Two oblique shocks are formed in a scramjet engine intake prior to entering the combustion chamber. The inlet Mach number is M1=5, the incoming air temperature is T1=216.67 K, p1=9.122 kPa, and A1=0.2 m^2. Calculate M3 in the combustion chamber ? if M2=4.0.

SOLVED:Two oblique shocks are formed in a scramjet engine intak…

SOLVED:The scramjet engine of Fig. 9.30 is supersonic throughout. A sketch is shown in Fig. C9.8. Test the following design. The flow enters at Ma=7 and air properties for 10,000 m altitude. Inlet area is 1 m^2, the minimum area is 0.1 m^2, and the exit area is 0.8 m^2 . If there is no combustion, (a) will the flow still be supersonic in the throat? Also, determine ( b ) the exit Mach number, (c) exit velocity, and ( d ) exit pressure.

SOLVED:The scramjet engine of Fig. 9.30 is supersonic throughout…

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