MCQOPTIONS
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MCQOPTIONS
This section includes 12 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
In which of these conditions there’s no formation of shock wave inside a convergent – divergent nozzle? |
| A. | Overexpanded |
| B. | Underexpanded |
| C. | Fully expanded |
| D. | Fully underexpanded |
| Answer» D. Fully underexpanded | |
| 2. |
Which of these conditions result in underexpanded nozzle? |
| A. | Pe = Pa |
| B. | Pe > Pa |
| C. | Pe < Pa |
| D. | Pe << Pa |
| Answer» C. Pe < Pa | |
| 3. |
What happens to the mass flow rate if the reservoir pressure is doubled? |
| A. | Doubled |
| B. | Remains same |
| C. | Becomes half |
| D. | Becomes one – fourth |
| Answer» B. Remains same | |
| 4. |
In case of the formation of shock in the divergent section of a C – D nozzle, the flow remains isentropic. |
| A. | True |
| B. | False |
| Answer» C. | |
| 5. |
What is the exit Mach number if the convergent nozzle is choked? |
| A. | 0 |
| B. | 1 |
| C. | 0.5 |
| D. | 1.5 |
| Answer» C. 0.5 | |
| 6. |
Which of this conditions is necessary to achieve flow in a nozzle? |
| A. | \(\frac {P_e}{P_0}\) < 1 |
| B. | \(\frac {P_e}{P_0}\) > 1 |
| C. | \(\frac {P_e}{P_0}\) = 1 |
| D. | \(\frac {P_e}{P_0}\) = 0 |
| Answer» B. \(\frac {P_e}{P_0}\) > 1 | |
| 7. |
If the given conditions for a nozzle are P01 = 1 atm, Pe = 0.3143 atm, then what is the ratio of exit area to throat area? |
| A. | 1.15 |
| B. | 1.5 |
| C. | 1.25 |
| D. | 1.115 |
| Answer» E. | |
| 8. |
For a nozzle with the following data \(\frac {A_e}{A_t}\) = 1.616, P01 = 1 atm, Pe = 0.947 atm, what is the the Mach number at the throat of the nozzle? |
| A. | 0.25 |
| B. | 0.50 |
| C. | 0.75 |
| D. | 0.58 |
| Answer» C. 0.75 | |
| 9. |
What happens in case of a choked flow? |
| A. | When flow becomes supersonic at the throat |
| B. | When flow is sonic and mass flow remains constant at the throat despite reducing exit pressure |
| C. | When the exit pressure is reduced to a point where the flow becomes subsonic at throat |
| D. | Normal shock is created at the inlet of the nozzle |
| Answer» C. When the exit pressure is reduced to a point where the flow becomes subsonic at throat | |
| 10. |
The area – Mach number relation yields how many solution(s) for a given Mach number? |
| A. | 1 |
| B. | 2 |
| C. | 3 |
| D. | 0 |
| Answer» C. 3 | |
| 11. |
In the area – Mach relation A < A* or A ≥ A*. |
| A. | True |
| B. | False |
| Answer» C. | |
| 12. |
For a flow in a duct, what is Mach number a function of? |
| A. | Local duct area to sonic throat area |
| B. | Sonic throat area to local duct area |
| C. | Local duct area to convergent duct area |
| D. | Local duct area to divergent duct area |
| Answer» B. Sonic throat area to local duct area | |