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. | Numerade