Question $9-$ Ramjet Operation $(15$ Points$)$: You are asked to calculate the operational parameters of an

ideal ramjet engine.

Flight Mach number is $2\mathrm{.}0.$ Burner exit temperature is $1700K.$ Flight altitude is $10km.$

Make the following assumptions:

Assume that the Mach number in the combustor is zero $($stations $2$ and $3)$

Ignore pressure losses in the combustor $($P$2=$P$3)$

Flow in the diffuser and nozzle are isentropic $($not through the shock wave though!$)$

Assume ideal gas and calorically perfect gas.

Perfect nozzle $($exit pressure is matched to the atmospheric pressure$)$

a$)$ Calculate the nozzle entrance $($burner exit$)$ pressure.

b$)$ Calculate the nozzle exit velocity.

c$)$ Calculate the heat addition $($per unit mass flow rate$)$ to the ramjet engine

d$)$ Calculate the overall efficiency of the ramjet engine

e$)$ Calculate the propulsive efficiency.

f$)$ If the nozzle throat diameter is $0\mathrm{.}2m,$ calculate the thrust of the ramjet system.