Consider a converging-diverging supersonic inlet, designed to cruise at Mach 1.8, at an altitude of 5,000 m. The inlet a

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Consider a converging-diverging supersonic inlet, designed to
cruise at
Mach 1.8, at an altitude of 5,000 m. The inlet area is 1 m2. The
airplane is
accelerated from Mach 0.2 to the design Mach number, when the shock
is
swallowed. Write a program or spreadsheet that calculates as
function of
flight Mach #:
a) the mass flow rate through the engine
b) the spillage around the engine, and
c) the percentage loss in stagnation pressure, including under
cruise
conditions. You can (but do not have to) use M# increments of
0.1.
Please also calculate to which Mach # you must ‘overspeed’ the
plane in
order to reduce the stagnations pressure loss during cruise by
50%.