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. | cm,le=-π \(\frac {\alpha }{2}\) |
| B. | cm,le=-\(\frac {c_l}{4}\) |
| C. | cm,le=-\(\frac {c_l}{2}\) |
| D. | cm,c/4=cm,le+\(\frac {c_l}{4}\) |
| Answer» D. cm,c/4=cm,le+\(\frac {c_l}{4}\) | |
| 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. | 2π rad |
| B. | 2π rad-1 |
| C. | π rad |
| D. | 0.11 degree |
| Answer» C. π rad | |
| 8. |
The lift coefficient for a thin symmetrical airfoil is given by______ |
| A. | cl = πα |
| B. | cl = π2α |
| C. | cl = 2πα |
| D. | cl = πα2 |
| Answer» D. cl = πα2 | |
| 9. |
Which of these is a wrong expression for the total circulation around a thin symmetric airfoil? |
| A. | Γ=\(\int_0^c\)γ(ξ)dξ |
| B. | Γ=\(\frac {c}{2} \int_0^{\pi }\)γ(θ)sinθ dθ |
| C. | Γ=cαV∞\(\int_0^c\)(1+cosθ)dθ |
| D. | Γ=cαV∞\(\int_0^{\pi }\)(1+cosθ)dθ |
| Answer» D. Γ=cαV∞\(\int_0^{\pi }\)(1+cosθ)dθ | |
| 10. |
What is the total circulation around the symmetric airfoil according to the thin airfoil theory? |
| A. | Γ=πα2cV∞ |
| B. | Γ=π2αcV∞ |
| C. | Γ=2παcV∞ |
| D. | Γ=παcV∞ |
| Answer» E. | |
| 11. |
Which of the following is the correct solution of the transformed fundamental equation of aerodynamics for a symmetrical airfoil? |
| A. | γ(θ)=2αV∞\(\frac {sin\theta }{1+cos\theta }\) |
| B. | γ(θ)=2αV∞\(\frac {1+cos\theta }{sin\theta }\) |
| C. | γ(θ)=2αV∞\(\frac {1-cos\theta }{sin\theta }\) |
| D. | γ(θ)=2αV∞\(\frac {cos\theta }{sin\theta }\) |
| Answer» C. γ(θ)=2αV∞\(\frac {1-cos\theta }{sin\theta }\) | |
| 12. |
The Kutta condition is not satisfied at the trailing edge where θ=π in transformed coordinates for a symmetrical airfoil. |
| A. | True |
| B. | False |
| Answer» C. | |