Consider the diffuser of a supersonic aircraft flying at M = 1.4 at such an altitude that the temperature is−20◦C and the atmospheric pressure is 50 kPa. Consider two possible ways in which the diffuser might operate, and for each case calculate the throat area required for a flow of 50 kg/s.

a. The diffuser operates as reversible adiabatic with subsonic exit velocity.
b. A normal shock stands at the entrance to the diffuser. Except for the normal shock the flow is reversible and adiabatic, and the exit velocity is subsonic. This is shown in Fig. P15.67. Assume a convergent-divergent diffuser with M = 1 at the throat.

Transcribed Image Text:

Normal shock- M = 1.4 FIGURE P15.67