Aramjet is shown in supersonic flight. the total pressure recovery is nd 0.90 and the nozzle is u expanded (note that po po). nder. calculate (a) ram temperature and pressure ratios, tr and π (b) the total temperature at the combustor exit, ts in k and the corresponding τλ (c) exhaust velocity, v9, in m/s (d) pressure thrust as a fraction of nozzle momentum nv9n9 thrust, 1.e., (e) the propulsive efficiency of the ramjet, np (note that the nozzle is not perfectly expanded, so you need to calculate v9eft) (1) thrust-specific fuel consumption, tsfc, in mg/s/n and lbm/hr/lbf