The exhaust gases from a rocket engine have a molar mass of 14. They can be assumed to behave as a perfect gas with a specific heat ratio of 1.28. These gases are accelerated through a nozzle. At some point in the nozzle where the cross-sectional area of the nozzle is 0.7 m^2, the pressure is 1000 kPa, the temperature is 500 degrees Celsius, and the velocity is 100 m/s. find the mass flow rate through the nozzle and the stagnation pressure and temperature. Also, find the highest velocity that could be generated by expanding this flow. If the pressure at some other point in the nozzle is 100 kPa, find the temperature and velocity at this point in the flow assuming the flow to be one-dimensional and isentropic.