MCQOPTIONS
Saved Bookmarks
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. |
What is the detrimental effect of high temperature hypersonic flow over a vehicle? |
| A. | Communication blackout |
| B. | Attitude problem |
| C. | Altitude problem |
| D. | Friction causing depletion of ablation |
| Answer» B. Attitude problem | |
| 2. |
Which of these surfaces is used for reentry vehicles at hypersonic speed? |
| A. | Aluminum |
| B. | Carbon |
| C. | Ablative surface |
| D. | Copper |
| Answer» D. Copper | |
| 3. |
What is viscous interaction? |
| A. | Interaction between viscous flow and boundary layer |
| B. | Interaction between inviscid flow and boundary layer |
| C. | Interaction between shock wave and inviscid flow |
| D. | Interaction between shock wave and viscous flow inside boundary layer |
| Answer» C. Interaction between shock wave and inviscid flow | |
| 4. |
Hypersonic boundary layers grow more rapidly compared to subsonic and supersonic boundary layers. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 5. |
How does viscous dissipation affect temperature inside the boundary layer? |
| A. | Increases |
| B. | Decreases |
| C. | No change |
| D. | First increases, then decreases |
| Answer» B. Decreases | |
| 6. |
What is viscous dissipation? |
| A. | Loss of kinetic energy due to viscous effect |
| B. | Loss of potential energy due to viscous effect |
| C. | Increase in kinetic energy due to increase in temperature |
| D. | Frictional drag |
| Answer» B. Loss of potential energy due to viscous effect | |
| 7. |
What is the entropy gradient at the nose region of a slender body at hypersonic flow? |
| A. | Very high |
| B. | Very low |
| C. | Negligible |
| D. | Infinity |
| Answer» B. Very low | |
| 8. |
How is the shock over a blunt body at hypersonic speed? |
| A. | Conical |
| B. | Curved |
| C. | Diamond |
| D. | Oblique |
| Answer» C. Diamond | |
| 9. |
In hypersonic flow, the shock waves often merge with the viscous boundary layer. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 10. |
How is the shock layer in case of hypersonic flow? |
| A. | Thin |
| B. | Thick |
| C. | Non existent |
| D. | Increases with increasing Mach number |
| Answer» B. Thick | |
| 11. |
For which of these Mach numbers is flow considered to be hypersonic? |
| A. | M < 1 |
| B. | M = 1 |
| C. | M > 5 |
| D. | 1 < M < 5 |
| Answer» D. 1 < M < 5 | |