man through the air which runs off compressed air (y = 1.4 and MW = 28.8 kg/kmol). The For your captsone project, your team is assigned to build a rocket propulsion system to propel a characteristic velocity C* is reported to be 500 m/s. An available nozzle with a throat diameter of 10 mm and exit diameter of 15 mm is available in the machine shop. Before launching, a pump is used to force air into the chamber until the pressure is at 680 kPa. Compute the area expansion ratio, exit Mach number and pressure, the thrust coefficient Ct, the initial thrust and Isp of the rocket at liftoff from sea level (p = 101 kPa).