MCQOPTIONS
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MCQOPTIONS
This section includes 13 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. |
Find tail efficiency if, dynamic pressure at tail and wing is 25Pa and 28Pa respectively. |
| A. | 0.892 |
| B. | 67.89% |
| C. | 12.54 |
| D. | 0.067 |
| Answer» B. 67.89% | |
| 2. |
An aircraft with wing aft tail configuration has tail efficiency of 0.95 and tail volume ratio of horizontal tail is 0.7. Determine pitching moment coefficient slope for the tail. Given lift curve slope of tail is 4.2 per rad. Consider downwash derivative as 0.6. |
| A. | -1.1172 per rad |
| B. | 2.45 |
| C. | 234.67 per degree |
| D. | 12.788 |
| Answer» B. 2.45 | |
| 3. |
A wing alone aircraft has aerodynamic centre pitching moment coefficient of -0.126. If lift coefficient at zero AOA is 0.38 then, find Cm0. Consider Xcg=0.3. |
| A. | -0.107 |
| B. | -7.89 |
| C. | 1.457 |
| D. | 0.9845 |
| Answer» B. -7.89 | |
| 4. |
If CLɑ wing = 1.2 per rad then, determine CMɑ. Given Xcg=0.29. |
| A. | 0.076 per rad |
| B. | 45 per rad |
| C. | 0.09 per rad |
| D. | 1.45 per rad |
| Answer» B. 45 per rad | |
| 5. |
If moment coefficient about aerodynamic centre of wing is -0.216 and lift coefficient of wing is 1.2. Find moment coefficient about cg. Given cg location as Xcg = 0.3. |
| A. | -0.156 |
| B. | 0.123 |
| C. | 0.56 |
| D. | -1.56 |
| Answer» B. 0.123 | |
| 6. |
A wing alone arrangement has wing lift curve slope of 2.65 per rad. Find slope of pitching moment coefficient. Given Xcg = 0.3. |
| A. | 0.025 per degree |
| B. | 0.03 per rad |
| C. | 45 per rad |
| D. | 0.0035 per degree |
| Answer» B. 0.03 per rad | |
| 7. |
For pitching moment coefficient diagram shown below which one will have positive trim AOA? |
| A. | Aircraft 1 |
| B. | Aircraft 2 |
| C. | Aircraft 3 |
| D. | Aircraft 3 and Curve 2 both |
| Answer» B. Aircraft 2 | |
| 8. |
Which of the aircraft will be statically stable based on following diagram? |
| A. | aircraft number 1 |
| B. | aircraft number 2 |
| C. | aircraft number 3 |
| D. | same static stability for all 3 aircrafts |
| Answer» B. aircraft number 2 | |
| 9. |
If aircraft continues to go farther away from equilibrium position after being disturbed then, the aircraft is called _______ |
| A. | unstable |
| B. | stable |
| C. | statically stable |
| D. | neutrally stable |
| Answer» B. stable | |
| 10. |
Object shown in the following diagram can be considered as __________ |
| A. | statically stable |
| B. | statically unstable |
| C. | stability can’t be guessed from diagram |
| D. | neutrally stable |
| Answer» B. statically unstable | |
| 11. |
Longitudinal stability means __________ |
| A. | stability about pitching axis |
| B. | stability about yawing axis |
| C. | stability about lateral axis |
| D. | stability about negative yawing axis |
| Answer» B. stability about yawing axis | |
| 12. |
How can we say that the aircraft has initial tendency to return to its original equilibrium position after being disturbed? |
| A. | If aircraft generates some restoring force or/and moment without any external help |
| B. | If restoring force is not generated to oppose the disturbance |
| C. | If lift is same as weight always |
| D. | If thrust loading is always unity |
| Answer» B. If restoring force is not generated to oppose the disturbance | |
| 13. |
Aircraft is said to be statically stable if __________ |
| A. | it has initial tendency to come back to its original equilibrium condition after being disturbed |
| B. | it has tendency to return to equilibrium state with the help of pilot’s input |
| C. | it has more lift than weight always |
| D. | it has more thrust than drag |
| Answer» B. it has tendency to return to equilibrium state with the help of pilot’s input | |