A $0\mathrm{.}5$m diameter ramjet engine having a diverging conical inlet diffuser and a converging exhaust nozzle is designed to operate at a flight Mach number $1\mathrm{.}7$ at $8$Km altitude. The total temperature of gas at entrance to the exhaust nozzle is $2000$K$.$ The fuel heating value is $45$MJ$/$Kg$.$ There is no lose in pressure that the air enters the combustion chamber with a Mach number $0\mathrm{.}2,$ that at the design condition a normal shock forms at the entrance of the diffuser, and that the nozzle is choked. Calculate the cross sectional area of the diffuser exit, exit area of the nozzle, mass flow rate of air, fuel air ratio, loss in total pressure, effective jet velocity, and thrust? Assume air as$$working$$medium$.$