MCQOPTIONS
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MCQOPTIONS
This section includes 10 Mcqs, each offering curated multiple-choice questions to sharpen your Rocket Propulsion knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
What is the nozzle throat diameter of a rocket having chamber pressure (Pc) of 3 MPa, mass flow rate (m) of 20 kg/s and characteristic velocity (c*) of 1500 m/s? |
| A. | 10 cm |
| B. | 11.3 cm |
| C. | 12.8 cm |
| D. | 25 cm |
| Answer» C. 12.8 cm | |
| 2. |
Which of the following is not part of a rocket nozzle? |
| A. | Convergent section |
| B. | Divergent section |
| C. | Throat section |
| D. | Staggering section |
| Answer» E. | |
| 3. |
What constitutes the exhaust gas at the nozzle exit of a chemical rocket engine? |
| A. | combustion products of the propellants |
| B. | A mixture of combustion products and surrounding air |
| C. | Surrounding air |
| D. | Propellants |
| Answer» B. A mixture of combustion products and surrounding air | |
| 4. |
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. |
| A. | 6.46 kg/s |
| B. | 103.1 kg/s |
| C. | 20.62 kg/s |
| D. | 32.33 kg/s |
| Answer» D. 32.33 kg/s | |
| 5. |
If mo denotes initial mass, mb denotes burnout mass, then what is the expression for mass ratio? |
| A. | (m<sub>o</sub>-m<sub>b</sub>)/m<sub>b</sub> |
| B. | (m<sub>o</sub>-m<sub>b</sub>)/m<sub>o</sub> |
| C. | m<sub>b</sub>/(m<sub>o</sub>-m<sub>b</sub>) |
| D. | m<sub>b</sub>/m<sub>o</sub> |
| Answer» E. | |
| 6. |
If C denotes effective exhaust velocity and Isp is specific impulse, then which of them is a better performance parameter? |
| A. | C |
| B. | Isp |
| C. | Both of them are equal |
| D. | Both of them are equivalent |
| Answer» E. | |
| 7. |
Which of the following variables is not useful in the determination of rocket effective exhaust velocity? |
| A. | Mass flow rate |
| B. | Exhaust velocity |
| C. | Rocket velocity |
| D. | Exit area |
| Answer» D. Exit area | |
| 8. |
Characteristic velocity is a performance parameter that relates to the efficiency of _____ |
| A. | nozzle |
| B. | combustion chamber |
| C. | injector |
| D. | casing |
| Answer» C. injector | |
| 9. |
What is the characteristic velocity of a rocket if the chamber pressure is 5 MPa, the nozzle throat diameter is 75 mm and the mass flow rate is 25 kg/s? |
| A. | 884 m/s |
| B. | 1768 m/s |
| C. | 3536 m/s |
| D. | 442 m/s |
| Answer» B. 1768 m/s | |
| 10. |
A rocket produces a total thrust of 20,000 N. If the mass flow rate of propellants is 16 kg/s, what will be effective exhaust velocity? |
| A. | 1250 m/s |
| B. | 2500 m/s |
| C. | 625 m/s |
| D. | 5000 m/s |
| Answer» B. 2500 m/s | |