Burning of the propellants take place in ______

nozzle

injector

engine casing

combustion chamber

Correct Answer : combustion chamber

Explanation : Propellants burn in the combustion chamber for both solid and liquid rocket engines. This burning can produce temperatures higher than melting points of many of the chamber wall materials. So, an effective cooling system is used to mitigate this issue.

Recently Updated in Rocket Propulsion Questions

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

10.12 cm²

11.20 cm²

12.10 cm²

21.10 cm²

Correct Answer : Option (A) : 10.12 cm²

Explaination : Nozzle throat area A_t = F/P₁C_F, where P₁ is the chamber pressure, C_F is the thrust coefficient and F is the total thrust provided by the rocket engine.
Then A_t = 10000/(5.2 x 10⁶ x 1.9)
= 10.12 cm².

The pressure drop across injector is usually set between _________ of the chamber pressure.

50 and 70%

45 and 65%

30 and 45%

15 and 25%

Correct Answer : Option (D) : 15 and 25%

Explaination : The pressure drop across the injector is set between 15 and 25% of the chamber pressure. This is done partly for obtaining high velocities of propellant injection. High velocities will help in easy atomization and droplet breakup which in turn helps in complete combustion.

Calculate the flow rate of LOX to the combustion chamber in a LOX-H2 rocket engine if the total propellant flow rate is 17 kg/s and mixture ratio is 3.2.

12.95 kg/s

13.67 kg/s

15.92 kg/s

17.81 kg/s

Correct Answer : Option (A) : 12.95 kg/s

Explaination : m?_o = m?_r/(r+1)
So m?_o = 17*3.2/4.2 = 12.95 kg/s.