MCQOPTIONS
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MCQOPTIONS
This section includes 13 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
The aerodynamic center for all the airfoils lies exactly at the quarter-chord always for all the given angle of attacks. |
| A. | True |
| B. | False |
| Answer» C. | |
| 2. |
When the lift becomes zero, the center of pressure of the cambered airfoil is at which point on the airfoil (consider given lengths are from the leading edge)? |
| A. | Quarter-chord length |
| B. | Mid-chord length |
| C. | 0 (i.e. at the leading edge) |
| D. | (i.e. the point does is not on the airfoil) |
| Answer» E. | |
| 3. |
For a cambered airfoil, the center of pressure does not vary with_____ |
| A. | Chord length |
| B. | Angle of attack |
| C. | The shape of the airfoil |
| D. | Location of the aerodynamic center |
| Answer» E. | |
| 4. |
The quarter-chord is the aerodynamic center for a cambered airfoil. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 5. |
The quarter-chord is the center of pressure for a cambered airfoil. |
| A. | False |
| B. | True |
| Answer» B. True | |
| 6. |
The quarter-chord moment coefficient for a cambered airfoil depends on______ |
| A. | Chord length |
| B. | Angle of attack |
| C. | The shape of the airfoil |
| D. | Center of pressure |
| Answer» D. Center of pressure | |
| 7. |
Given an angle of attack 5 , A1=1.5, A2=2 and the chord length is 5m, the moment coefficient about the quarter-chord is_____ |
| A. | ( frac { pi }{8} ) |
| B. | ( frac { pi }{4} ) |
| C. | ( frac {- pi }{8} ) |
| D. | ( frac { pi }{4} ) |
| Answer» B. ( frac { pi }{4} ) | |
| 8. |
The relation between lift coefficient and moment coefficient about the leading edge is_______ |
| A. | c<sub>m,le</sub>=-( ( frac {c_l}{2}+ frac { pi }{4} )(A<sub>1</sub>-A<sub>2</sub>)) |
| B. | c<sub>m,le</sub>=-( ( frac {c_l}{4}+ frac { pi }{4} )(A<sub>1</sub>-A<sub>2</sub>)) |
| C. | c<sub>m,le</sub>=-( ( frac {c_l}{4} )+(A<sub>1</sub>-A<sub>2</sub>)) |
| D. | c<sub>m,le</sub>=( ( frac {c_l}{2}+ frac { pi }{4} )(A<sub>1</sub>-A<sub>2</sub>)) |
| Answer» C. c<sub>m,le</sub>=-( ( frac {c_l}{4} )+(A<sub>1</sub>-A<sub>2</sub>)) | |
| 9. |
The moment coefficient for a thin cambered airfoil about the leading edge is given by______ |
| A. | c<sub>m,le</sub>=-0.5 (2A<sub>0</sub>+A<sub>1</sub>) |
| B. | c<sub>m,le</sub>=- (A<sub>0</sub>+A<sub>1</sub>+A<sub>2</sub>) |
| C. | c<sub>m,le</sub>=-0.5 (A<sub>0</sub>+A<sub>1</sub>-0.5A<sub>2</sub>) |
| D. | c<sub>m,le</sub>=- (2A<sub>2</sub>+A<sub>1</sub>) |
| Answer» D. c<sub>m,le</sub>=- (2A<sub>2</sub>+A<sub>1</sub>) | |
| 10. |
The zero-lift angle of attack for a thin, cambered airfoil increases in magnitude with the increasing camber of the airfoil. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 11. |
Which of the following does not hold for the zero-lift angle of attack? |
| A. | It is a negative value |
| B. | Denoted by <sub>L=0</sub> |
| C. | It is zero for a symmetric airfoil |
| D. | Does not depend on the slope of the camber line |
| Answer» E. | |
| 12. |
The coefficient of lift for a thin, cambered airfoil with A0=0.2 and A1=1.12 is____ |
| A. | 1.52 |
| B. | 1 |
| C. | 0.52 |
| D. | 2 |
| Answer» B. 1 | |
| 13. |
The lift curve slope for a thin, cambered airfoil is 2 . |
| A. | True |
| B. | False |
| Answer» B. False | |