Question

1. A fixed-geometry supersonic inlet starts at a Mach number of 3. After starting, the cruise Mach number is 2, and the operating shock is positioned at a location where the area is 10% larger than the throat. a) Assuming the flow is ideal except for shock losses, find the inlet stagnation pressure ratio poz/poa during cruise. b) During cruise, the Mach number at the exit of the diffuser M, is required to be 0.3. Determine the ratio of the areas at the diffuser exit to that at the inlet (find A/A), and the static pressure ratio pz/p.

Answer 1

Answer:

(a) Stagnation to static pressure ratio = 7.82

(b) A2/A1=1.2

Static Pressure Ratio= 1.865

Explanation:

The detailed answer is given in the attached files.