MCQOPTIONS
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MCQOPTIONS
This section includes 12 Mcqs, each offering curated multiple-choice questions to sharpen your Aircraft Design knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
Determine the corrections or otherwise of the following assertion [A] and reason [R]:
|
| A. | nReason[R]: Wing twist is used to improve stall properties at tip. |
| B. | Both [A] and [R] are true and [R] is the correct reason for [A] |
| C. | Both [A] and [R] are true but [R] is not the correct reason for [A] |
| D. | [A] is true but [R] is false |
| E. | [A] is false but [R] is true |
| Answer» C. Both [A] and [R] are true but [R] is not the correct reason for [A] | |
| 2. |
Excessive dihedral can produce _____ |
| A. | dutch roll |
| B. | thrust |
| C. | pitch |
| D. | deflection at nose |
| Answer» B. thrust | |
| 3. |
What is the function of wing twist? |
| A. | To improve stall characteristics at tip |
| B. | To reduce lift by tail |
| C. | To provide lofting |
| D. | To increase engine thrust |
| Answer» B. To reduce lift by tail | |
| 4. |
If root chord is 2m and tip chord is 0.9m then, find taper ratio. |
| A. | 0.45 |
| B. | 0.55 |
| C. | 0.65 |
| D. | 0.25 |
| Answer» B. 0.55 | |
| 5. |
The ratio of tip and root chord is called ____ |
| A. | taper ratio |
| B. | sweep |
| C. | aspect ratio |
| D. | slope |
| Answer» B. sweep | |
| 6. |
Canard pusher aircraft uses wing sweep to change location of aerodynamic centre. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 7. |
Wing sweep is used to ____ |
| A. | increase critical mach number |
| B. | decrease critical mach number |
| C. | increase lofting |
| D. | increase drafting |
| Answer» B. decrease critical mach number | |
| 8. |
An aircraft with elliptic wing planform has parasite drag coefficient as 0.9. Lift coefficient of wing is 1.8 and aspect ratio is 8.5. Find total drag coefficient for the wing. |
| A. | 1.021 |
| B. | 0.9 |
| C. | 0.121 |
| D. | 0.25 |
| Answer» B. 0.9 | |
| 9. |
An aircraft with elliptic wing planform has parasite drag coefficient as 0.6. Lift coefficient of wing is 0.25 and aspect ratio is 7.5. If induced drag co-efficient is 0.0235 then, find total drag coefficient for the wing. |
| A. | 0.06235 |
| B. | 0.5235 |
| C. | 0.6 |
| D. | 0.0235 |
| Answer» B. 0.5235 | |
| 10. |
Let s consider an aircraft has statistically determined aspect ratio of 8.1. Aircraft has canard which gives contribution of 10% for total lift. Determine the aspect ratio of wing. |
| A. | 9 |
| B. | 0.9 |
| C. | 10 |
| D. | 8.1 |
| Answer» B. 0.9 | |
| 11. |
If aspect ratio of wing is 8 and S=0.1m2 then, what will be the span of wing? |
| A. | 0.89m |
| B. | 0.89cm |
| C. | 0.89 |
| D. | 0.89inch |
| Answer» B. 0.89cm | |
| 12. |
For high aspect ratio strength of the wing tip vortex is low. |
| A. | True |
| B. | False |
| Answer» B. False | |