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. |
If I want to locate my minimum pressure at 0.5 of chord c then _____________ |
| A. | NACA 6512 |
| B. | NACA 652132 |
| C. | NACA 65211 |
| D. | NACA 0009 |
| Answer» C. NACA 65211 | |
| 2. |
Location of aerodynamic centre for low speed airfoil is ____ |
| A. | at quarter chord point |
| B. | at quarter chord from leading edge |
| C. | there is no such place |
| D. | at half of chord |
| Answer» B. at quarter chord from leading edge | |
| 3. |
Determine the corrections or otherwise of the following assertion [A] and reason [R]:
|
| A. | nReason[R]: Cambered airfoils can produce positive lift at 0 AOA. |
| 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» B. Both [A] and [R] are true and [R] is the correct reason for [A] | |
| 4. |
A NACA 22104 airfoil is operating at AOA = 3 . The lift-coefficient at this AOA is 0.15. Determine the value of angle of attack at designed lift co-efficient. |
| A. | 4.36 |
| B. | 4.36rad |
| C. | 0.05 rad |
| D. | 0.05 |
| Answer» B. 4.36rad | |
| 5. |
An airfoil is operated with flow velocity such that the pressure on upper and lower surface are 30 Pa and 15 Pa respectively. If chord is 1m then, what will be the lift produced by this airfoil? |
| A. | 15N |
| B. | 15KN |
| C. | 25N |
| D. | 30 Pa |
| Answer» B. 15KN | |
| 6. |
The maximum lift co-efficient for NACA 19584 (chord=2.5m) airfoil is____ |
| A. | 0.15 |
| B. | 0.315 |
| C. | 0.15N |
| D. | 0.3N |
| Answer» B. 0.315 | |
| 7. |
What will be the location of maximum camber for NACA 13250 with chord length of 2m? |
| A. | 0.32m from leading edge |
| B. | 0.32 from trailing edge |
| C. | 0.32m from trailing edge |
| D. | 0.32 from leading edge |
| Answer» B. 0.32 from trailing edge | |
| 8. |
Let s consider we need to design supersonic aircraft then, which type of airfoil should be adopted? |
| A. | Supersonic airfoil |
| B. | Symmetric airfoil |
| C. | Bluff shape |
| D. | Thicker airfoil |
| Answer» B. Symmetric airfoil | |
| 9. |
An airfoil is such that the drag produced by airfoil is 25N. Airfoil has chord of 2m and is experiencing dynamic pressure of 10Pa. Find the value of drag co-efficient for airfoil. |
| A. | 1.25 |
| B. | 1.6 |
| C. | 2.5 |
| D. | 2.51 |
| Answer» B. 1.6 | |
| 10. |
Laminar bucket is region where ____ |
| A. | flow remains laminar |
| B. | turbulent is produced |
| C. | drag increases drastically |
| D. | lift is reduced drastically |
| Answer» B. turbulent is produced | |
| 11. |
What do you mean by double cambered airfoil? |
| A. | Airfoil with flat lower surface |
| B. | Airfoil with flat upper and lower surface |
| C. | Airfoil with curved upper and lower surface |
| D. | Only upper surface is curved |
| Answer» D. Only upper surface is curved | |
| 12. |
Pressure on the upper surface is _________ |
| A. | lower than lower surface |
| B. | higher than lower surface |
| C. | always 30.25 times lower surface |
| D. | always same |
| Answer» B. higher than lower surface | |