Bissoy.com
Doctors Medicines MCQs Q&A

For increased operating chamber pressure, the length of the combustion chamber ________ and the nozzle throat area _________ if the diameter of the combustion chamber (assume the shape to be cylindrical) is fixed and the thrust remains constant.

For increased operating chamber pressure, the length of the combustion chamber ________ and the nozzle throat area _________ if the diameter of the combustion chamber (assume the shape to be cylindrical) is fixed and the thrust remains constant. Correct Answer decreases; decreases

The combustion chamber length will decrease because the combustion chamber volume decreases with the chamber pressure for the same thrust. It will also lead to a decrease in the nozzle throat area.

Related Questions

Consider the following statements in connection with thrust bearings: 1) Cylindrical thrust bearings have higher coefficient of friction than ball thrust bearings. 2) Taper rollers cannot be employed for thrust bearings. 3) Double-row thrust ball bearing is not possible 4) Lower race, outer race and retainer are readily separable in thrust bearings. Which of the above statements are correct?
Rocket A has twice the pressure thrust of rocket B while it has half the momentum thrust as that of B. If the momentum thrust of B is 5 times its pressure thrust, find the ratio of total thrust of A to B.
Determine the nozzle throat area for a rocket engine producing a total thrust of 10 kN, chamber pressure of 5.2 MPa and thrust coefficient of 1.9.
A sphere of diameter 42 cm is melted and bullets are formed from it. The bullet has circular cylindrical shape from one side and conical from other side. The radius of the base of the cylindrical part of the bullet is 6 cm and the cylindrical part has thrice as much length as the conical part. Find how many such bullets can be formed if the curved surface area of the cylindrical part of a bullet is 79.2 cm2.
Determine the chamber volume if the characteristic length of a thrust chamber is 150 cm and nozzle throat area is 0.25m2.
Determine the rocket thrust coefficient for a total thrust of 20 kN, chamber pressure of 500 kPa and a throat diameter of 10 cm.
If the divergence angle for a conical nozzle is 30°, nozzle exit diameter is 30 cm, exit pressure is 10% more than the ambient pressure, mass flow rate is 14 kg/s and the jet exhaust velocity is 700 m/s, determine the total thrust of the engine under standard sea level operating conditions.
A rocket has a throat area of 10 mm2 and nozzle exit area of 25 mm2. If the mass flow rate of its propellants is 2 kg/s, exit velocity is 30 m/s, and if exit pressure is twice the standard atmospheric pressure at sea level, what will be the total thrust?
Determine the chamber pressure for a rocket engine if the thrust coefficient is 1.8, the throat area is 0.2 m2 and the total thrust is 20000 N.
For a conical nozzle of throat diameter 0.007 m, exit cross-section diameter 0.02 m, and divergent section length of 0.038 m, determine the nozzle semi-divergence angle.