A 2D supersonic inlet (Fig. 7.9) is constructed with two ramps each of which deflects the flow through 15◦. Following the second oblique shock, a fixed throat inlet is used for internal compression. The inlet is designed to start for a flight Mach number of 2.5. Determine the stagnation pressure recovery, assuming  (a) that the inlet starts (no normal shock at the entrance) and (b) that the inlet does not start (normal shock at the entrance). Also, determine the ratio of the entrance area to throat area.

Assume that the throat Mach number is 1 in both the cases.

Transcribed Image Text:

Fig. 7.9 Illustration of a 2D mixed inlet with a fixed throat