The following conditions refer to a rocker propellant flow rate = 193 kg/s. Thrust chamber pressure 27 bar and temperature 3000k. Nozzle exit diameter = 600 mm. Nozzle exit pressure = 1.1 bar and ambient pressure = 1.013 bar. Thrust produced = 380 kN. a) b) c) Find the effective jet velocity, actual jet velocity, specific impulse and the specific propellant consumption. Recalculate the values of thrust and specific impulse for an altitude of 20000 m. The rocket speed is 2500 Kmph and the heat of reaction of the propellant is 6500 KJ/kg, find for case a) i.e. ambient pressure of 1.013 bar find np, nth, and no.