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. |
Which of the following is correct to trim an aircraft at positive AOA? |
| A. | Cm0 > 0 |
| B. | Cm0 < 0 |
| C. | Cm0 will not affect positive trim AOA |
| D. | Every value of cm0 will trim at positive AOA |
| Answer» B. Cm0 < 0 | |
| 2. |
Determine the corrections or otherwise of the following Assertion [A] and Reason [R]:Assertion [A]: For longitudinal static stability of an aircraft, slope of moment curve should be negative. |
| A. | nReason[R]: Positive slope will result in more static stability than negative slope. Hence, slope should be positive always. |
| 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» D. [A] is true but [R] is false | |
| 3. |
Elevator control power is given by _____ |
| A. | ( frac{dCm}{d delta e} ) |
| B. | Zero lift drag |
| C. | T = CD0 + K*CL |
| D. | DCL/ |
| Answer» B. Zero lift drag | |
| 4. |
If CM0 is -0.052 and lift coefficient at zero angle CL0 is 0.92 then, find CMac. Consider rectangular wing. |
| A. | -0.282 |
| B. | 0.98 |
| C. | 2.5 |
| D. | 7.89 |
| Answer» B. 0.98 | |
| 5. |
A rectangular wing has chord of 2m. Fond neutral point for this wing. |
| A. | 50 cm |
| B. | 290 cm |
| C. | 189 cm |
| D. | 267 m |
| Answer» B. 290 cm | |
| 6. |
Find the appropriate value of pitching moment coefficient derivative if lift curve slope is 0.032 per degree and Xcg is 0.3. Consider neutral point is located at 60 % of chord from leading edge. |
| A. | -0.0096 per degree |
| B. | -7 per degree |
| C. | 2.56 per degree |
| D. | 0.1 |
| Answer» B. -7 per degree | |
| 7. |
If SM = 0.12 and cg is located at 20% chord from l.e. then, find appropriate neutral point location. |
| A. | 0.32 |
| B. | 0.87 |
| C. | 2.3 |
| D. | 1.54 |
| Answer» B. 0.87 | |
| 8. |
Determine required static margin if lift curve slope is 6.5 per rad and pitching moment coefficient slope as -0.58 per rad. |
| A. | 8.9% |
| B. | 78% |
| C. | 0.89 |
| D. | 8.403 |
| Answer» B. 78% | |
| 9. |
Determine trim angle if, trim lift coefficient is 0.75 and lift curve slope is 4.5per rad. Consider elevator deflection as 1.056 per rad and trim elevator angle of 0.020 rad. |
| A. | 0.1619 rad |
| B. | 0.1619 |
| C. | 2.98 rad |
| D. | 34.23 rad |
| Answer» B. 0.1619 | |
| 10. |
Thrust will affect the stability of the aircraft. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 11. |
Canard will provide longitudinal static stability. |
| A. | False |
| B. | True |
| Answer» B. True | |
| 12. |
If an aircraft has lift curve slope of 4.76 per rad and moment coefficient curve slope of -0.116 per rad then, find the location of neutral point. Consider Xcg=0.3. |
| A. | 0.324 |
| B. | 0.9825 |
| C. | 23.45 |
| D. | 45.7 |
| Answer» B. 0.9825 | |
| 13. |
Following diagram represents __________ |
| A. | cg position influence on moment coefficient curve |
| B. | lift curve |
| C. | drag polar |
| D. | thrust required minimum |
| Answer» B. lift curve | |
| 14. |
An aircraft wing is experiencing AOA of 5 . If downwash due to wing is 2.6 then, how much angle is being seen by tail of the aircraft? |
| A. | 2.4 |
| B. | 4.5 |
| C. | 6.7 |
| D. | 1.23 |
| Answer» B. 4.5 | |