A rocket engine burns liquid hydrogen and liquid oxygen in a 3.4:1 ratio (by mass: 3.4 kg Oxygen per kg Hydrogen). The Pressure is 6.895 MPa in the chamber, the temperature is 2959K, the average molecular mass of the products is 8.9kg/kmol, and the ratio of specific heats for the products is 1.26. What is the characteristic velocity of the chamber products? If the engine throat is 0.1m in diameter, what is the mass flow of the engine?
For the engine in previous problem, if the nozzle expands the flow to 50kPa exit pressure, what is the thrust coefficient, thrust and specific impulse for this rocket at: a) sea level, b) the ideal expansion altitude, and c) in vacuum?