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. |
In Steady level unaccelerated flight, lift is equal to weight. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 2. |
A jet engine is designed to operate at endurance of 12hrs. If weight fraction is 1.6 and jet engine has tsfc C as 0.00021 per second then, find at which lift to drag ratio that can satisfy above criteria. |
| A. | 19.3 |
| B. | 18 |
| C. | 12 |
| D. | 12.6 |
| Answer» B. 18 | |
| 3. |
A prop driven aircraft has propeller efficiency of 0.92 and C as 0.000745 1/m. If lift to drag ratio is 14 and weight fraction as 1.145 then, find range of the propeller driven aircraft. |
| A. | 2340.95m |
| B. | 2340.5miles |
| C. | 2340km |
| D. | 2500miles |
| Answer» B. 2340.5miles | |
| 4. |
A propeller aircraft has wing loading of 30 unit and is operating with density of 1.21 unit. Determine velocity for maximum loiter. Consider K/CD0 as 0.1. |
| A. | 3unit |
| B. | 5unit |
| C. | 9unit |
| D. | 10unit |
| Answer» B. 5unit | |
| 5. |
An aircraft has maximum lift to drag ratio of 15. If we want to fly aircraft for best range then, find the best value of aerodynamic efficiency to achieve above mentioned result. |
| A. | 12.9 |
| B. | 13.5 |
| C. | 15 |
| D. | 12.1 |
| Answer» B. 13.5 | |
| 6. |
Find instantaneous range of a jet propelled aircraft if lift to drag ratio is 12 and weight fraction at cruise W1/W0 is 1.9. Consider cruise speed of 120m/s and SFC of 0.00161 per second. |
| A. | 574km |
| B. | 574m |
| C. | 574miles |
| D. | 574ft |
| Answer» B. 574m | |
| 7. |
Find the value of lift coefficient to ensure power required minimum condition for cruise if CD0/K is given as 0.480. |
| A. | 1.2 |
| B. | 2.1 |
| C. | 1.7 |
| D. | 7.5 |
| Answer» B. 2.1 | |
| 8. |
Determine the value of drag at which we can have minimum power if given reference area is 10m2 and zero lift drag coefficient is 0.5. Consider q as 120Pa. |
| A. | 2400N |
| B. | 1.25 |
| C. | 9.85 |
| D. | 4500 KN |
| Answer» B. 1.25 | |
| 9. |
If power required at sea level altitude is 2005W then, determine power required at altitude at which density ratio is 0.9. |
| A. | 2.113KW |
| B. | 211115W |
| C. | 2354W |
| D. | 500W |
| Answer» B. 211115W | |
| 10. |
An aircraft is operating with CL of 1.5 and has power required of 120W. If we want to reduce the power required by half then, find the value of CL at this power required condition. Consider steady level flight. |
| A. | 2.38 |
| B. | 1.946 |
| C. | 9.45 |
| D. | 5.59 |
| Answer» B. 1.946 | |
| 11. |
An aircraft has L/D as 12 and thrust required at this value is 100N. Now if L/D has doubled then what will be the new thrust required? |
| A. | 50N |
| B. | 500N |
| C. | 100 N |
| D. | 12.5N |
| Answer» B. 500N | |
| 12. |
Calculate how much power will require to maintain cruise speed of 120 m/s if thrust required is 1KN. Consider steady level flight. |
| A. | 120KW |
| B. | 110N |
| C. | 120N |
| D. | 129W |
| Answer» B. 110N | |