Bissoy.com
Doctors Medicines MCQs Q&A

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?

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? Correct Answer 62.53 N

Total thrust = momentum thrust + pressure thrust. Momentum thrust = 2*30 = 60 N Pressure thrust = (Pe-Pa)*Ae = 101325*25/1000000 = 2.53 N Total thrust = 60 + 2.53 = 62.53 N.

Related Questions

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.
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.
For a rocket traveling at 700 m/s having an exhaust velocity of 1.4 km/s, exhaust gas density of 0.3 kg/m3, nozzle throat diameter of 0.14 cm and nozzle exit diameter of 25 cm, find the total mass flow rate of the propellants.
If the exit pressure is thrice the atmospheric pressure for a rocket A and if it is twice for rocket B, what will be the ratio of pressure thrust of rocket A to that of B?
The average weight of a class of 12 students is 57 kgs. Two students of weights 48 kgs and 68 kgs are replaced by 2 new students having weights 52 kgs and 55 kgs. What is the new average weight of the class?
A rocket engine moving at 500 m/s produces a total thrust of 9563 N, consuming propellants at the rate of 4.55 kg/s. The energy content of the propellants is 5.35 MJ/kg. Find the effective exhaust velocity.
The formula to determine the height of the rocket above the ground at any time during the rocket's flight is given by: h = 119t - 7t2 where t = the time, in seconds, that has elapsed since the rocket was launched, and h = the height, in meters, of the rocket above the ground at time t. The value of h was 0 when the rocket hit the ground. How many seconds after the rocket was launched did it hit the ground?
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.
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?
For a rocket having 95% combustion efficiency, total chemical power of 17MW, a mass flow rate of propellants of 15 kg/s, and effective jet exhaust velocity of 1443 m/s, find the internal efficiency of rocket propulsion.