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. |
Afterburning can lead to ozone layer depletion. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 2. |
At which of the following altitudes does the infrared emissions from the mixing zone of the rocket exhaust higher? |
| A. | near sea level |
| B. | Stratospheric region |
| C. | Just outside the atmosphere |
| D. | Outer space |
| Answer» B. Stratospheric region | |
| 3. |
Which of the following is the mixing layer of a nozzle core flow? |
| A. | Inviscid inner core flow |
| B. | Viscous outer core flow |
| C. | Inviscid outer core flow |
| D. | Viscous inner core flow |
| Answer» C. Inviscid outer core flow | |
| 4. |
If A is the pre-exponential factor, n is the temperature exponent, Ea is the activation energy, then the expression for forward rate constant according to Arrhenius law is ______ |
| A. | k<sub>f</sub> = AT<sup>n</sup> exp(-E<sub>a</sub>/RT) |
| B. | k<sub>f</sub> = T exp(-E<sub>a</sub>A/RT<sup>n</sup>) |
| C. | k<sub>f</sub> = AT<sup>n</sup> exp(-E<sub>a</sub>/RT<sup>n</sup>) |
| D. | k<sub>f</sub> = AT exp(-E<sub>a</sub>/nRT) |
| Answer» B. k<sub>f</sub> = T exp(-E<sub>a</sub>A/RT<sup>n</sup>) | |
| 5. |
For strong emission signature of exhaust plumes, afterburning of fuel-rich gases is optimum for invisibility. |
| A. | True |
| B. | False |
| Answer» C. | |
| 6. |
Which of the following correspond to the spectral bands of CO2 and H2O respectively in the IR signature of rocket exhaust plumes? |
| A. | 2.7 m and 4.3 m |
| B. | 7.2 m and 3.4 m |
| C. | 4.3 m and 2.7 m |
| D. | 3.4 m and 7.2 m |
| Answer» D. 3.4 m and 7.2 m | |
| 7. |
Determine the mass ratio (Burnout mass/ Initial mass) of a vehicle in a gravitation less space if its velocity is boosted from 800 m/s to 1600 m/s and the effective rocket exhaust velocity is 2000 m/s. |
| A. | 0.85 |
| B. | 0.33 |
| C. | 0.67 |
| D. | 0.25 |
| Answer» D. 0.25 | |
| 8. |
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. |
| A. | 61.33 kPa |
| B. | 67.98 kPa |
| C. | 45.67 kPa |
| D. | 55.56 kPa |
| Answer» E. | |
| 9. |
What are the primary sources of radiation in a chemical rocket engine? |
| A. | Excitation of molecules in the combustion chamber |
| B. | De-excitation of internal modes of gas molecules |
| C. | Rapid combustion of injector fuel |
| D. | Shock layer at the nozzle exit |
| Answer» C. Rapid combustion of injector fuel | |
| 10. |
In which of these following altitudes does a rocket exhibit narrow pencil shaped exhaust plume? |
| A. | Low altitude |
| B. | Above atmosphere |
| C. | Outer space |
| D. | During launch |
| Answer» B. Above atmosphere | |