MCQOPTIONS
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MCQOPTIONS
This section includes 14 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 circulation at the center for an elliptical wing distribution does not depend upon ________ |
| A. | Lift distribution |
| B. | Density of fluid at center |
| C. | Free-stream velocity |
| D. | Total span length |
| Answer» C. Free-stream velocity | |
| 2. |
Which of the following is not implied by the elliptical lift distribution? |
| A. | Chord length is constant along the span |
| B. | Induced angle of attack is zero for infinite wing span |
| C. | Downwash is zero for infinite wing span |
| D. | Constant downwash along the span |
| Answer» B. Induced angle of attack is zero for infinite wing span | |
| 3. |
Which is the wrong implication of the elliptical lift distribution for a wing? |
| A. | Circulation varies elliptically along span |
| B. | Span length does not affect circulation |
| C. | Lift is zero at the tips |
| D. | Maximum lift is at the center |
| Answer» C. Lift is zero at the tips | |
| 4. |
The induced drag (Di’) in terms of lift per unit span (L’) for a finite wing is_____ |
| A. | Di’=L’sin sinαi |
| B. | Di’=L’αi |
| C. | Di’=πL’αi |
| D. | Di’=L’cos cosαi |
| Answer» B. Di’=L’αi | |
| 5. |
Downwash for an elliptic wing circulation distribution is constant. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 6. |
The incorrect statement in relation to the fundamental equation of Prandtls lifting line theory is_____ |
| A. | Geometric AoA is sum of effective AoA and induced AoA |
| B. | Integro-differential equation |
| C. | Γ is known |
| D. | Finite wing design, geometric AoA and free-stream velocity is known |
| Answer» D. Finite wing design, geometric AoA and free-stream velocity is known | |
| 7. |
The lift coefficient for the airfoil section on a wing ______ |
| A. | Depends on local lift slope for airfoil |
| B. | Is same for the entire wing |
| C. | Is equal to the aerodynamic twist |
| D. | Is constant always |
| Answer» B. Is same for the entire wing | |
| 8. |
The induced angle of attack in terms of flow parameters for a wing is_____ |
| A. | αi=\(\frac {w}{V_∞}\) |
| B. | αi=\(\frac {2w}{V_∞}\) |
| C. | αi=\(\frac {V_∞}{w}\) |
| D. | αi=\(\frac {w}{V_∞}\) |
| Answer» B. αi=\(\frac {2w}{V_∞}\) | |
| 9. |
For the case of infinite horseshoe vortices along the lifting line, a vortex sheet exists which_________ |
| A. | Is formed by continuous trailing vortices |
| B. | Is perpendicular to free-stream velocity |
| C. | Total strength is zero |
| D. | Equal and opposite trailing vortices |
| Answer» C. Total strength is zero | |
| 10. |
The infinite downwash at the wing tips for a single horseshoe vortex in Prandtls lifting line theory was a wrong result. Which of the following does not relate to the correction made? |
| A. | Superimposition of horseshoe vortices |
| B. | Lifting line along the span |
| C. | Trailing vortices only at the tip |
| D. | Different length of bound vortices |
| Answer» D. Different length of bound vortices | |
| 11. |
The incorrect statement regarding the downwash for a single horseshoe vortex in Prandtl’s lifting line theory is____ |
| A. | Downwash has contribution from trailing vortices |
| B. | Downwash becomes infinite at the tips |
| C. | Downwash is given by w=\(\frac {-\Gamma}{4\pi } \frac {b}{(\frac {b}{2})^2-y^2}\) |
| D. | The contribution of two semi-infinite trailing vortices is same as an infinite vortex |
| Answer» E. | |
| 12. |
The downwash along the wing in the downward direction in Prandtl’s lifting line theory comes from______ |
| A. | Bound vortex |
| B. | Horseshoe vortex |
| C. | Free vortex |
| D. | Trailing vortices |
| Answer» E. | |
| 13. |
Circulation varies along the lifting line. |
| A. | False |
| B. | True |
| Answer» C. | |
| 14. |
According to the reasoning given by Prandtl for his lifting line theory, finite wing is like a ________ |
| A. | Bound vortex |
| B. | Horseshoe vortex |
| C. | Free vortex |
| D. | Trailing vortex |
| Answer» B. Horseshoe vortex | |