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This section includes 10 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 how many categories is the supersonic wind tunnel classified into? |
A. | 2 |
B. | 3 |
C. | 4 |
D. | 6 |
Answer» B. 3 | |
2. |
What is the ratio of throat area of diffuser to nozzle in supersonic wind tunnel with flow at Mach 2.7? |
A. | 0.4236 |
B. | 0.8338 |
C. | 2.36 |
D. | 1.199 |
Answer» D. 1.199 | |
3. |
In which scenario is the throat area of both the nozzle and diffuser the same? |
A. | Ideal isentropic diffuser |
B. | Ideal adiabatic diffuser |
C. | Ideal isobaric diffuser |
D. | Ideal Isochoric diffuser |
Answer» B. Ideal adiabatic diffuser | |
4. |
What is the relation between the nozzle A1t and diffuser throat area A2t in the supersonic wind tunnel? |
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> | |
5. |
The nozzle throat area is same as the diffuser throat area. |
A. | True |
B. | False |
Answer» C. | |
6. |
In reality what happens due to the interaction of the oblique shock waves with the boundary layer on the walls of the diffuser? |
A. | Higher total pressure loss |
B. | Reduction of speed |
C. | Total pressure increase |
D. | Reduced skin friction drag |
Answer» B. Reduction of speed | |
7. |
Normal shock diffuser is less efficient than the oblique shock diffuser. |
A. | True |
B. | False |
Answer» B. False | |
8. |
How many throat/throats are there in a supersonic wind tunnel? |
A. | 1 |
B. | 2 |
C. | 3 |
D. | 4 |
Answer» C. 3 | |
9. |
Which of these is not a part of supersonic wind tunnel? |
A. | Nozzle |
B. | Test section |
C. | Diffuser |
D. | Test model |
Answer» E. | |
10. |
Which nozzle is used in supersonic wind tunnel? |
A. | Convergent |
B. | Divergent |
C. | Convergent Divergent |
D. | Conical |
Answer» D. Conical | |