MCQOPTIONS
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MCQOPTIONS
This section includes 7 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 wing is designed to operate with free stream velocity of 20m/s and air density of 1.225 kg/m3. Find aerodynamic efficiency of given wing. Consider S as 8 m2, CL as 0.9 and CD as 1.25. |
| A. | 0.72 |
| B. | 2 |
| C. | 3 |
| D. | 5.23 |
| Answer» B. 2 | |
| 2. |
Cambered wing has minimum drag coefficient of 0.05 and constant K of 0.023. If CL is 0.8 then find the value of CD. Given minimum drag occurs at CL of 0.1. |
| A. | 0.06127 |
| B. | 6.1 |
| C. | 61.2 |
| D. | 0.6721 |
| Answer» B. 6.1 | |
| 3. |
For a symmetrical airfoil drag coefficient at zero lift is 0.05 and induced drag coefficient is 0.0025. Find the total drag coefficient. |
| A. | 0.0525 |
| B. | 0.45 |
| C. | 5.25 |
| D. | 52.5 |
| Answer» B. 0.45 | |
| 4. |
If Lift produced by wing is 350N then, determine lift coefficient. Given q = 35Pa and S=8.5 m2. |
| A. | 1.174 |
| B. | 2.8 |
| C. | 5.6 |
| D. | 4.37 |
| Answer» B. 2.8 | |
| 5. |
If an aircraft is operating with dynamic pressure of the free stream q=20Pa and has area of wing is 10m2 then evaluate drag experience by the aircraft. Given drag coefficient is 0.9. |
| A. | 180 N |
| B. | 345 N |
| C. | 234 N |
| D. | 567 N |
| Answer» B. 345 N | |
| 6. |
If an aircraft as pitching moment of 10 Nm and dynamic pitching moment is about 8.25Nm. Find the moment coefficient Cm. |
| A. | 1.21 |
| B. | 3 |
| C. | 5.62 |
| D. | 0.0921 |
| Answer» B. 3 | |
| 7. |
How do you define the lift coefficient? |
| A. | Ratio of aerodynamic lift to the dynamic lift |
| B. | Lift to drag |
| C. | Wing lift to weight of aircraft |
| D. | Thrust to weight |
| Answer» B. Lift to drag | |