MCQOPTIONS
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MCQOPTIONS
This section includes 11 Mcqs, each offering curated multiple-choice questions to sharpen your Aircraft Performance knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
Trailing edge deflection decreases the camber of the aerofoil section. |
| A. | True |
| B. | False |
| Answer» C. | |
| 2. |
Leading edge flap deflection has the effect of increasing lift curve to a higher stalling angle of attack. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 3. |
What is stall buffet condition? |
| A. | It is an aerodynamic vibration caused due to separation or turbulent airflow |
| B. | it is a condition in which the separation is laminar |
| C. | It is a condition in which the flow separation is not considered |
| D. | It is a condition in which the turbulence is not considered |
| Answer» B. it is a condition in which the separation is laminar | |
| 4. |
What is the value of Cl of a symmetric airfoil if the angle of attack is 5°? |
| A. | 0.548 |
| B. | 0.0548 |
| C. | 3.1416 |
| D. | 31.416 |
| Answer» B. 0.0548 | |
| 5. |
Which of the following is a correct condition when the angle of attack is beyond stalling angle? |
| A. | Drag is greater than lift |
| B. | Weight is less than lift |
| C. | Drag is less than lift |
| D. | Weight is less than thrust |
| Answer» B. Weight is less than lift | |
| 6. |
What is meant by stalling angle of attack? |
| A. | The angle at which we get maximum lift |
| B. | The angle at which we get maximum drag |
| C. | The angle at which we get minimum lift |
| D. | The angle at which we get minimum drag |
| Answer» B. The angle at which we get maximum drag | |
| 7. |
The lift curve slope is inversely proportional to thickness and directly proportional to aspect ratio. |
| A. | True |
| B. | False |
| Answer» C. | |
| 8. |
What is the theoretical value of lift curve slope of a flat airfoil? |
| A. | 2π per radian |
| B. | 4aπ per radian |
| C. | 3π per radian |
| D. | π per radian |
| Answer» B. 4aπ per radian | |
| 9. |
In the case of cambered airfoil the value of α0 is positive. |
| A. | True |
| B. | False |
| Answer» C. | |
| 10. |
The zero-lift angle of attack is zero if the aerofoil is symmetric. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 11. |
Which of the following is the correct formula for lift of an aircraft? |
| A. | L=\(\frac{1}{2}\)ρV2SCl |
| B. | L=\(\frac{1}{2}\)V2SCl |
| C. | L=\(\frac{1}{2}\)ρV2Cl |
| D. | L=\(\frac{1}{2}\)PV2SCl |
| Answer» B. L=\(\frac{1}{2}\)V2SCl | |