A new supersonic passenger aircraft is being designed for flight Mach number 2.5 at an alt...

A new supersonic passenger aircraft is being designed for flight Mach number 2.5 at an altitude where the ambient pressure and temperature are 9 kPa and 220 K, respectively. The engine inlet configuration shown below allows for double oblique shock deceleration followed by a zone of subsonic deceleration. The Mach number is 0.5 at the engine inlet plane . Losses in the subsonic diffuser are neglected. Determine:

a.The Mach numbers M1 and M2 in the zones and  shown on the drawing,

b.the wave angles θ1 and θ2, also shown on the drawing,

c.the overall stagnation pressure ratio poi/poa,

d.the overall static pressure ratio pi/pa,

e.the velocity ratio ci/c2 for the subsonic diffuser, and

f.the cross-sectional area Ai(m2) at the engine inlet plane if the engine mass flow rate is 500 kg/s