2. A rocket engine operating on a gas generator engine cycle has the following test data: Engine thrust 100,100 N Engine specific impulse 250.0 sec Gas generator flow 3.00% of total propellant flow Specific impulse of turbine exhaust flowing through a low area ratio nozzle 100.2 sec Determine the specific impulse and thrust for the single thrust chamber Answers: 254.6 sec and 98,899 N