MCQOPTIONS
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MCQOPTIONS
This section includes 11 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. | A<sub>t2</sub> = A<sub>t1</sub> |
| B. | A<sub>t2</sub> > A<sub>t1</sub> |
| C. | A<sub>t2</sub> < A<sub>t1</sub> |
| D. | A<sub>t2</sub> A<sub>t1</sub> = 1 |
| Answer» C. A<sub>t2</sub> < A<sub>t1</sub> | |
| 2. |
What is the diffuser efficiency for hypersonic conditions? |
| A. | <sub>D</sub> = 1 |
| B. | <sub>D</sub> > 1 |
| C. | <sub>D</sub> < 1 |
| D. | <sub>D</sub> = 1/2 |
| Answer» D. <sub>D</sub> = 1/2 | |
| 3. |
What is the formula to compute the efficiency of diffusers? |
| A. | <sub>D</sub> = ( frac {( frac {p_{d_0}}{p_0})_{actual }}{( frac {p_{0_2}}{p_{01}})_{normal , shock , at , M_e}} ) |
| B. | <sub>D</sub> = ( frac {( frac {p_{d_0}}{p_0})_{actual }}{( frac {p_{0_2}}{p_{01}})_{oblique , shock , at , M_e}} ) |
| C. | <sub>D</sub> = ( frac {( frac {p_{0_2}}{p_{01}})_{normal , shock , at , M_e}}{( frac {p_{d_0}}{p_0})_{actual }} ) |
| D. | <sub>D</sub> = ( frac {( frac {p_{0_2}}{p_{01}})_{oblique , shock , at , M_e}}{( frac {p_{d_0}}{p_0})_{actual }} ) |
| Answer» B. <sub>D</sub> = ( frac {( frac {p_{d_0}}{p_0})_{actual }}{( frac {p_{0_2}}{p_{01}})_{oblique , shock , at , M_e}} ) | |
| 4. |
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 | |
| 5. |
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 | |
| 6. |
Normal shock diffuser is more efficient than the oblique shock diffuser. |
| A. | True |
| B. | False |
| Answer» C. | |
| 7. |
What is the relation between the entry and exit entropy of an actual supersonic diffuser? |
| A. | s<sub>1</sub> = s<sub>2</sub> |
| B. | s<sub>1</sub> > s<sub>2</sub> |
| C. | s<sub>1</sub> < s<sub>2</sub> |
| D. | s<sub>1</sub> s<sub>2</sub> = 1 |
| Answer» D. s<sub>1</sub> s<sub>2</sub> = 1 | |
| 8. |
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. | |
| 9. |
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 | |
| 10. |
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 | |
| 11. |
Diffuser is only applicable for incoming subsonic flow. |
| A. | True |
| B. | False |
| Answer» C. | |