On a test stand, a nozzle operates is entropically with a chamber pressure of 2 MPa and chamber temperature of 2500 K. If the products of combustion are assumed to behave as a perfect gas with k = 1.3 and molar mass = 20 kg/kmol, determine the rocket motor thrust that is transmitted to the stand. Assume the nozzle exit area to be 0.01 m2 and the back pressure to be 50 kPa.