MCQOPTIONS
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MCQOPTIONS
This section includes 14 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
How is diffuser throat area At2 related to the nozzle throat area At1? |
| A. | At2 = At1 |
| B. | At2 > At1 |
| C. | At2 < At1 |
| D. | At2 At1 = 1 |
| Answer» C. At2 < At1 | |
| 2. |
What is the diffuser efficiency for hypersonic conditions? |
| A. | ηD = 1 |
| B. | ηD > 1 |
| C. | ηD < 1 |
| D. | ηD = 1/2 |
| Answer» D. ηD = 1/2 | |
| 3. |
What is the diffuser efficiency of a normal shock diffuser? |
| A. | 1 |
| B. | 0 |
| C. | Inifinty |
| D. | \(\frac {1}{2}\) |
| Answer» B. 0 | |
| 4. |
What is the formula to compute the efficiency of diffusers? |
| A. | ηD = \(\frac {(\frac {p_{d_0}}{p_0})_{actual }}{(\frac {p_{0_2}}{p_{01}})_{normal \, shock \, at \, M_e}}\) |
| B. | ηD = \(\frac {(\frac {p_{d_0}}{p_0})_{actual }}{(\frac {p_{0_2}}{p_{01}})_{oblique \, shock \, at \, M_e}}\) |
| C. | ηD = \(\frac {(\frac {p_{0_2}}{p_{01}})_{normal \, shock \, at \, M_e}}{(\frac {p_{d_0}}{p_0})_{actual }}\) |
| D. | ηD = \(\frac {(\frac {p_{0_2}}{p_{01}})_{oblique \, shock \, at \, M_e}}{(\frac {p_{d_0}}{p_0})_{actual }}\) |
| Answer» B. ηD = \(\frac {(\frac {p_{d_0}}{p_0})_{actual }}{(\frac {p_{0_2}}{p_{01}})_{oblique \, shock \, at \, M_e}}\) | |
| 5. |
Which of these factors contribute to additional total pressure losses inside the oblique shock diffuser? |
| A. | Abrupt change of convergent – divergent sections |
| B. | Shock wave interaction with walls |
| C. | Isentropic flow |
| D. | Presence of normal shock |
| Answer» C. Isentropic flow | |
| 6. |
How is the flow compressed in an ideal supersonic wind tunnel inside a diffuser? |
| A. | Isentropic |
| B. | Adibatic |
| C. | Isochoric |
| D. | Isobaric |
| Answer» B. Adibatic | |
| 7. |
Normal shock diffuser is more efficient than the oblique shock diffuser. |
| A. | True |
| B. | False |
| Answer» C. | |
| 8. |
What is the relation between the entry and exit entropy of an actual supersonic diffuser? |
| A. | s1 = s2 |
| B. | s1 > s2 |
| C. | s1 < s2 |
| D. | s1 s2 = 1 |
| Answer» D. s1 s2 = 1 | |
| 9. |
Which of these results in decrease of the flow inside the actual supersonic diffuser? |
| A. | Test section |
| B. | Convergent nature |
| C. | Divergent nature |
| D. | Shock waves |
| Answer» E. | |
| 10. |
Which of these processes is involved in slowing down the air inside the subsonic diffuser? |
| A. | Adiabatic compression |
| B. | Adiabatic expansion |
| C. | Isentropic expansion |
| D. | Isothermal compression |
| Answer» C. Isentropic expansion | |
| 11. |
Why is ideal supersonic diffuser not feasible? |
| A. | Presence of shock waves |
| B. | Varying cross – sectional area |
| C. | Varying throat area |
| D. | Choked flow |
| Answer» B. Varying cross – sectional area | |
| 12. |
Which of these properties remain constant in the ideal isentropic supersonic diffuser? |
| A. | Total pressure |
| B. | Velocity |
| C. | Mach number |
| D. | Mass flow |
| Answer» B. Velocity | |
| 13. |
Diffuser is only applicable for incoming subsonic flow. |
| A. | True |
| B. | False |
| Answer» C. | |
| 14. |
What is the role of the diffuser? |
| A. | Increase the flow velocity after test section |
| B. | Decrease the flow velocity after test section |
| C. | Increase the flow velocity inside test section |
| D. | Decrease the flow velocity inside the test section |
| Answer» C. Increase the flow velocity inside test section | |