In problem 15-3-16 [BNQ] (a) determine the thrust if the outside pressure is 0 kPa. (b) What-if Scenario: What would the thrust be if the normal shock did not exist?
Problem 15-3-16
A rocket nozzle has an exit-to-throat area ratio of 4.0. The exhaust gases are generated in a combustion chamber with stagnation pressure equal to 4 MPa and stagnation temperature equal to 2000 K. Assume the working fluid to behave as a perfect gas with k = 1.3 and molar mass = 20 kg/kmol. Determine (a) the rocket exhaust velocity and (b) the mass flow rate. Assume isentropic steady flow except at the nozzle exit where a normal shock is located as shown in the accompanying figure.