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. |
A prop driven A/C has BHP/W as 0.08. If density ratio is 0.2 and take off lift coefficient is 3 then find take-off parameter for the aircraft. Given wing loading W/s = 35. |
| A. | 700 |
| B. | 800 |
| C. | 900 |
| D. | 500 |
| Answer» B. 800 | |
| 2. |
Jet aircraft with CD=0.01+0.02CL2 is performing loiter. Find wing loading for maximum loiter if, AR=8.5, e=0.7 and dynamic pressure is 25Pa. |
| A. | 10.80 |
| B. | 11.80 |
| C. | 12.80 |
| D. | 13.08 |
| Answer» B. 11.80 | |
| 3. |
Which of the following is correct for maximum jet range? |
| A. | W/S = (q* sqrt{ pi eARCD0/3} ) |
| B. | W/S = (q* sqrt{ pi eAR} ) |
| C. | W/S = (q* sqrt{ pi eARCD0} ) |
| D. | W/S = q |
| Answer» B. W/S = (q* sqrt{ pi eAR} ) | |
| 4. |
For prop aircraft at maximum range what will be the wing loading. Given CD0=0.02, aspect ratio as 8, e=0.6 and q=39.20Pa. |
| A. | 21.5 |
| B. | 12.5 |
| C. | 1.05 |
| D. | 25 |
| Answer» B. 12.5 | |
| 5. |
An aircraft has catapult end speed of 30m/s and wind over deck as 20m/s. If maximum CL is 2.6 and density is 1.22 then, find catapult wing loading. |
| A. | 3276.859 |
| B. | 327 |
| C. | 32 |
| D. | 2 |
| Answer» B. 327 | |
| 6. |
Which of the following is correct for a jet aircraft take-off parameter (TOP)? |
| A. | TOP = ( frac{W/S}{ CL frac{T}{W}} ) |
| B. | TOP = ( frac{1}{ CL frac{T}{W}} ) |
| C. | TOP = ( frac{2}{ CL frac{T}{W}} ) |
| D. | TOP = ( frac{W}{ CL frac{T}{W}} ) |
| Answer» B. TOP = ( frac{1}{ CL frac{T}{W}} ) | |
| 7. |
Determine wing loading for civil aircraft if lift-off speed is 80m/s and maximum lift coefficient is 2.8. |
| A. | 9071.07 |
| B. | 9111 |
| C. | 911 |
| D. | 91 |
| Answer» B. 9111 | |
| 8. |
An aircraft is flying with wing loading of 50 and maximum CL as 2.4. If density is 1.225 then, find the stall speed of the aircraft. |
| A. | 5.832m/s |
| B. | 5.823 |
| C. | 5.632m/s |
| D. | 5.632 |
| Answer» B. 5.823 | |
| 9. |
As a designer I want to reduce the empty weight of my aircraft. Therefore I will ______ |
| A. | increase wing loading |
| B. | decrease wing loading |
| C. | wing loading has no effect |
| D. | will reduce by exactly half |
| Answer» B. decrease wing loading | |
| 10. |
Low wing loading will provide ___________ |
| A. | more space for fuel storage in wing |
| B. | more space of fuel storage in cabin |
| C. | less fuel storage |
| D. | less lift |
| Answer» B. more space of fuel storage in cabin | |
| 11. |
Design lift coefficient is determined by wing loading. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 12. |
Wing loading will affect _____________ |
| A. | only stall speed |
| B. | only ground roll |
| C. | stall speed, climbing, ground roll etc |
| D. | only climb |
| Answer» D. only climb | |
| 13. |
Wing loading is ratio of ___________ |
| A. | weight of the aircraft and the reference area of wing |
| B. | reference area of wing and power of engine |
| C. | lift to drag |
| D. | aerodynamic force thrust to drag |
| Answer» B. reference area of wing and power of engine | |