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. |
Which of the following gases show a strong emission band in the region of radiant heat transfer? |
| A. | Ammonia |
| B. | Hydrogen |
| C. | Oxygen |
| D. | Nitrogen |
| Answer» B. Hydrogen | |
| 2. |
Which of the following is the correct expression for energy radiated by a body (Assume ε to be emissivity, A to be surface area, T to be temperature, f to be geometric factor) |
| A. | E = (1/f)εσAT4 |
| B. | E = fεσAT4 |
| C. | E = (1/f)εσAT2 |
| D. | E = fεσAT2 |
| Answer» C. E = (1/f)εσAT2 | |
| 3. |
In which of the following ignition techniques does the system use a solid propellant squib or grain of few seconds of burning duration? |
| A. | Spark plug ignition |
| B. | Pyrotechnic ignition |
| C. | Ignition by electrically heated wires |
| D. | Precombustion chamber ignition |
| Answer» C. Ignition by electrically heated wires | |
| 4. |
Which of the following is a realistic value of the discharge coefficient? |
| A. | 0.5 |
| B. | 1.5 |
| C. | 5.5 |
| D. | 10.5 |
| Answer» B. 1.5 | |
| 5. |
The pressure drop across injector is usually set between _________ of the chamber pressure. |
| A. | 45 and 65% |
| B. | 30 and 45% |
| C. | 15 and 25% |
| D. | 5 and 15% |
| Answer» D. 5 and 15% | |
| 6. |
If the semi-divergence angle of a conical nozzle is 15°, throat diameter is 8.326 cm and exit area is 0.54 m2, determine the nozzle length. |
| A. | 139.2 cm |
| B. | 239.1 cm |
| C. | 312.9 cm |
| D. | 231.9 cm |
| Answer» B. 239.1 cm | |
| 7. |
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. | 10.12 cm2 |
| B. | 12.10 cm2 |
| C. | 11.20 cm2 |
| D. | 21.10 cm2 |
| Answer» B. 12.10 cm2 | |
| 8. |
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. |
| A. | 11.33 kg/s |
| B. | 15.92 kg/s |
| C. | 12.95 kg/s |
| D. | 13.67 kg/s |
| Answer» D. 13.67 kg/s | |
| 9. |
Find the fuel flow rate for a total propellant flow of 10 kg/s and a mixture ratio of 2.3. |
| A. | 4.71 kg/s |
| B. | 7.41 kg/s |
| C. | 1.47 kg/s |
| D. | 4.17 kg/s |
| Answer» E. | |
| 10. |
Determine the propellant mass flow rate for a TSFC of 3200 kg/Ns and a total thrust of 50 kN. |
| A. | 21.65 kg/s |
| B. | 12.56 kg/s |
| C. | 16.52 kg/s |
| D. | 15.62 kg/s |
| Answer» E. | |