A rocket motor is fired on a test stand. Hot exhaust gases leave the exit with a velocity of 700 m/s at a mass flow rate (m⋅) of 10 kg/s. The exit area is 0.01 m2 and the exit pressure is 50 kPa. For an ambient pressure of 100 kPa, determine the rocket motor thrust that is transmitted to the stand. Assume steady state and one-dimensional flow.