Design a supersonic nozzle to operate at 10 km altitude with an area ratio of 8.0. for the hot gas take to = 3000 k, r = 378 j/kg-k and k = 1.3. determine the exit mach number, exit velocity, and exit temperature, as well as the chamber pressure. if this chamber pressure is doubled, what happens to the thrust and the exit velocity? assume no change in gas properties. how close to optimum nozzle expansion is this nozzle?