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. |
We are using the airfoil in the aircraft as _____ |
| A. | it is a streamline shape which provides better aerodynamics |
| B. | it is a random shape can be changed to rectangular as well |
| C. | it is easy to make than rectangular |
| D. | it is not a streamline body |
| Answer» B. it is a random shape can be changed to rectangular as well | |
| 2. |
Which of these is not part of an airfoil? |
| A. | Leading edge |
| B. | Chord |
| C. | Camber |
| D. | Fins |
| Answer» B. Chord | |
| 3. |
Pitching moment co-efficient for an airfoil is given by _____ |
| A. | lift*area |
| B. | drag*area |
| C. | section pitching moment/dynamic pitching moment |
| D. | lift/dynamic moment |
| Answer» D. lift/dynamic moment | |
| 4. |
An airfoil is subjected to the flow with temperature of 288.16K and flow is ideal. The velocity at the leading edge is ____ |
| A. | 0m/s |
| B. | 250m/s |
| C. | 288.16m/s |
| D. | 16.882m/s |
| Answer» B. 250m/s | |
| 5. |
Consider a NACA 2812 airfoil. It is operating with flow velocity of 900m/s with chord of 1m. What should be the maximum thickness of this airfoil? |
| A. | 0.12m |
| B. | 0.21m |
| C. | 0.9m |
| D. | 28.12m |
| Answer» B. 0.21m | |
| 6. |
Find location of aerodynamic centre from leading edge if, chord is 10m and airfoil has flow velocity of 0.2 M. |
| A. | 2.5 m |
| B. | 0.2 m |
| C. | 5 m |
| D. | 10 m |
| Answer» B. 0.2 m | |
| 7. |
If an airfoil has lift of 200 N at 10 AOA, then what is induced drag produced by airfoil at that AOA? |
| A. | 0 N |
| B. | 100 |
| C. | 0 |
| D. | 100 N |
| Answer» B. 100 | |
| 8. |
A symmetric airfoil is operating with flow velocity of 350m/s. The lift produced by the airfoil is 21 N at 0.008 rad AOA. If chord is c m then, what will be the pressure difference across the airfoil? |
| A. | 21/c Pa |
| B. | 21c/2 N |
| C. | 21 Pa |
| D. | 21c N |
| Answer» B. 21c/2 N | |
| 9. |
Airfoil is a streamline shape. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 10. |
Which of the following is not type of an airfoil? |
| A. | Symmetric |
| B. | Camber |
| C. | Whitcomb |
| D. | Vortex |
| Answer» E. | |
| 11. |
An aerofoil is operating with flow velocity of 100m/s. Aerofoil is symmetric and is at 0 AOA. Determine lift produced by this aerofoil. |
| A. | 10.5 N |
| B. | 0 N |
| C. | 50 N |
| D. | 100N |
| Answer» C. 50 N | |
| 12. |
Aerofoil affects the performance parameters of aircraft. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 13. |
The cross-sectional shape of wing is called _____ |
| A. | airfoil |
| B. | circle |
| C. | camber |
| D. | chord |
| Answer» B. circle | |