MCQOPTIONS
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MCQOPTIONS
This section includes 12 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
Aerodynamic center and center of pressure coincide for all the airfoils. |
| A. | False |
| B. | True |
| Answer» B. True | |
| 2. |
For a flat plate, aerodynamic center and center of pressure coincide. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 3. |
Select the incorrect statement for a thin, symmetric airfoil out of the following. |
| A. | Quarter-chord is the aerodynamic center |
| B. | Quarter-chord is the center of pressure |
| C. | Moment about quarter-chord depends on the angle of attack |
| D. | Moment about quarter-chord is zero |
| Answer» D. Moment about quarter-chord is zero | |
| 4. |
The coefficient of moment about the quarter chord is zero for a symmetric airfoil. This implies____ |
| A. | Quarter-chord is the center of pressure |
| B. | Quarter-chord is the center of mass |
| C. | Quarter-chord has zero forces acting on it |
| D. | Total lift is zero at quarter-chord |
| Answer» B. Quarter-chord is the center of mass | |
| 5. |
Which of the following is an incorrect relation for a flat plate? |
| A. | c<sub>m,le</sub>=- ( frac { alpha }{2} ) |
| B. | c<sub>m,le</sub>=- ( frac {c_l}{4} ) |
| C. | c<sub>m,le</sub>=- ( frac {c_l}{2} ) |
| D. | c<sub>m,c/4</sub>=c<sub>m,le</sub>+ ( frac {c_l}{4} ) |
| Answer» D. c<sub>m,c/4</sub>=c<sub>m,le</sub>+ ( frac {c_l}{4} ) | |
| 6. |
Given an angle of attack 5 and c = 5m, the moment coefficient about the leading edge is_____ |
| A. | -0.137 |
| B. | -0.685 |
| C. | -7.8 |
| D. | -0.27 |
| Answer» B. -0.685 | |
| 7. |
The lift curve slope for a flat plate is_____ |
| A. | 2 rad |
| B. | 2 rad<sup>-1</sup> |
| C. | rad |
| D. | 0.11 degree |
| Answer» C. rad | |
| 8. |
The lift coefficient for a thin symmetrical airfoil is given by______ |
| A. | c<sub>l</sub> = |
| B. | c<sub>l</sub> = <sup>2</sup> |
| C. | c<sub>l</sub> = 2 |
| D. | c<sub>l</sub> = <sup>2</sup> |
| Answer» D. c<sub>l</sub> = <sup>2</sup> | |
| 9. |
Which of these is a wrong expression for the total circulation around a thin symmetric airfoil? |
| A. | = ( int_0^c ) ( )d |
| B. | = ( frac {c}{2} int_0^{ pi } ) ( )sin u2061 d |
| C. | =c V<sub> </sub> ( int_0^c )(1+cos )d |
| D. | =c V<sub> </sub> ( int_0^{ pi } )(1+cos )d |
| Answer» D. =c V<sub> </sub> ( int_0^{ pi } )(1+cos )d | |
| 10. |
What is the total circulation around the symmetric airfoil according to the thin airfoil theory? |
| A. | = <sup>2</sup>cV<sub> </sub> |
| B. | = <sup>2</sup> cV<sub> </sub> |
| C. | =2 cV<sub> </sub> |
| D. | = cV<sub> </sub> |
| Answer» E. | |
| 11. |
Which of the following is the correct solution of the transformed fundamental equation of aerodynamics for a symmetrical airfoil? |
| A. | ( )=2 V<sub> </sub> ( frac {sin u2061 theta }{1+cos theta } ) |
| B. | ( )=2 V<sub> </sub> ( frac {1+cos theta }{sin u2061 theta } ) |
| C. | ( )=2 V<sub> </sub> ( frac {1-cos u2061 theta }{sin theta } ) |
| D. | ( )=2 V<sub> </sub> ( frac {cos theta }{sin theta } ) |
| Answer» C. ( )=2 V<sub> </sub> ( frac {1-cos u2061 theta }{sin theta } ) | |
| 12. |
The Kutta condition is not satisfied at the trailing edge where = in transformed coordinates for a symmetrical airfoil. |
| A. | True |
| B. | False |
| Answer» C. | |