MCQOPTIONS
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MCQOPTIONS
This section includes 14 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 net velocity if sideslip angle is 3.8 degree and [v] = 4.2 unit. |
| A. | 63.23 unit |
| B. | 100 unit |
| C. | 100.23 unit |
| D. | 102.623 unit |
| Answer» B. 100 unit | |
| 2. |
Determine sideslip angle for a steady level unaccelerated flight with [u, v, w] = [80, 2, 4.5]. |
| A. | 1.43 |
| B. | 5.4 |
| C. | 5 |
| D. | 12.32 |
| Answer» B. 5.4 | |
| 3. |
Find resultant velocity if [u, v, w] = [80, 2, 4.5]. Consider steady level flight. |
| A. | 80.151 |
| B. | 90 |
| C. | 10.52 |
| D. | 100.159 |
| Answer» B. 90 | |
| 4. |
Find sideslip angle if [u, v, w] = [100, 5, 2.5]. Consider steady level flight. |
| A. | 2.86 |
| B. | 4.5 |
| C. | 4.7 |
| D. | 2.1 |
| Answer» B. 4.5 | |
| 5. |
Determine the value of rudder deflection r for an aircraft which is flying in north with the velocity of 60.5 m/s under the crosswind of 5m/s from east to west with Cn =0.02/deg and Cn r = -0.045/deg, where sideslip angle is -4.72 . |
| A. | -2.09 |
| B. | 3.5 |
| C. | -4.5 |
| D. | -4.74 |
| Answer» B. 3.5 | |
| 6. |
An aircraft is flying in the north direction at a velocity of 60.5m/s under cross wind from the east to west of 5m/s. If the value of Cn =0.02/deg, where. Find sideslip angle . |
| A. | -4.72 |
| B. | -5 |
| C. | 4.7 |
| D. | 3.18 |
| Answer» B. -5 | |
| 7. |
Aircraft can suffer from adverse yaw during rolling. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 8. |
An aircraft experiences sideslip of 4 and side wash at vertical tail is 1.2 . What will be the AOA at vertical tail? |
| A. | 5.2 |
| B. | 6.89 |
| C. | 1.2 |
| D. | 21.3 |
| Answer» B. 6.89 | |
| 9. |
Rolling moment will influence _______ |
| A. | aircraft lateral stability |
| B. | longitudinal stability |
| C. | pitch axis stability |
| D. | pitching stability only |
| Answer» B. longitudinal stability | |
| 10. |
Which is the minimum requirement for pure directional stability? |
| A. | Slope of yawing moment curve positive |
| B. | Negative lift curve slope |
| C. | Negative pitching moment coefficient curve slope |
| D. | Positive zero lift pitching moment coefficient |
| Answer» B. Negative lift curve slope | |
| 11. |
If aircraft is in straight flight (cruise with lift of 100N) then, what will be the value of net rolling moment? Consider ideal conditions. |
| A. | 0 unit |
| B. | 12 Nm |
| C. | 23 unit |
| D. | 25 N/m |
| Answer» B. 12 Nm | |
| 12. |
Stability about roll axis is called _____________ |
| A. | lateral stability |
| B. | directional stability |
| C. | longitudinal stability |
| D. | elevator control |
| Answer» B. directional stability | |
| 13. |
Yawing moment is positive if __________ |
| A. | right wing goes back |
| B. | right wing comes forward |
| C. | if nose pitches up |
| D. | if nose pitches down |
| Answer» B. right wing comes forward | |
| 14. |
Stability about yawing axis is called as __________ |
| A. | directional stability |
| B. | lateral stability |
| C. | longitudinal stability |
| D. | pitching moment stability |
| Answer» B. lateral stability | |