List of top Propulsion Questions asked in GATE Aerospace Engineering

In a static test, a turbofan engine with bypass ratio of 9 has core hot exhaust speed 1.5 times that of fan exhaust speed. The engine is operated at a fuel–air ratio of $f=0.03$. Both the fan and the core streams have no pressure thrust. The ratio of fan thrust to thrust from the core engine is (round off to one decimal place).

In a single stage turbine, the hot gases come out of stator/nozzle at a speed of 500 m/s and at an angle of 70 degrees with the turbine axis as shown. The design speed of the rotor blade is 250 m/s at the mean blade radius. The rotor blade angle, \( \beta \), at the leading edge is _________ degrees (round off to one decimal place).

A high-pressure-ratio multistage axial compressor encounters an extreme loading mismatch during starting. Which of the following technique(s) can be used to alleviate this problem?

The region of highest static temperature in a rocket engine and the region of highest heat flux are _______, respectively.

The point of maximum entropy on a Fanno-curve in a Temperature–Entropy (T–s) diagram represents the