An external-compression supersonic inlet with a single ramp operates in critical mode as shown. The flight speed is 750(m)/(sec) where the ambient air (static) temperature and pressure are 224 K and 20 kPa respectively. Neglect all losses except those occurring due to shocks. Also, use gamma =1.4 and R_(air )=287 (m^(2))/(s^(2)(K)) for this proble

Question

An external-compression supersonic inlet with a single ramp operates in critical mode as shown. The flight speed is

750(m)/(sec)

where the ambient air (static) temperature and pressure are 224 K and 20 kPa respectively. Neglect all losses except those occurring due to shocks. Also, use

\gamma =1.4

and

R_(air )=287

(m^(2))/(s^(2)(K))

for this problem. (a) Calculate inlet total pressure recovery due to shocks. In other words, what is the stagnation pressure ratio,

(p_(02))/(p_(000))=

? (show or explain your work) (b) Estimate the inlet adiabatic efficiency for this case. In other words, what is

\eta _(d)=

?

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