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 lift per unit span for a thin, cambered airfoil with Γ=10\(\frac {m^2}{s}\), ρ∞=1.0255\(\frac {kg}{m^3}\), V∞=10\(\frac {m}{s}\) is____ |
| A. | 0 |
| B. | 102.55\(\frac {N}{m}\) |
| C. | 102.55N |
| D. | 55\(\frac {N}{m}\) |
| Answer» B. 102.55\(\frac {N}{m}\) | |
| 2. |
The lift per unit span for a thin, cambered airfoil with α=5°, A0=0.65, A1=1 is____ |
| A. | L’ = cπ\(V_∞^2\)ρ∞ (1.15) |
| B. | L’ = cπ\(V_∞^2\)ρ∞ (1.65) |
| C. | L’ = cπ\(V_∞^2\)ρ∞ (-0.35) |
| D. | L’ = cπ\(V_∞^2\)ρ∞ (0.15) |
| Answer» B. L’ = cπ\(V_∞^2\)ρ∞ (1.65) | |
| 3. |
For α=5°, A0=1 and A1=-2 total circulation Γ for a thin cambered airfoil equals______ |
| A. | 0 |
| B. | 2πcV∞ |
| C. | πcV∞ |
| D. | 2.5πcV∞ |
| Answer» B. 2πcV∞ | |
| 4. |
The correct formula for the Fourier sine series appearing in the solution of thin airfoil theory is_____ |
| A. | An=\(\frac {2}{\pi }\int_0^{\pi }\frac {dz}{dx}\) cosn∅ d∅ |
| B. | An=\(\frac {1}{\pi }\int_0^{\pi }\frac {dz}{dx}\) cosn∅ d∅ |
| C. | An=\(\frac {2}{\pi }\int_0^{2\pi }\frac {dz}{dx}\) cosn∅ d∅ |
| D. | An=α-\(\frac {1}{\pi }\int_0^{\pi }\frac {dz}{dx}\) cosn∅ d∅ |
| Answer» B. An=\(\frac {1}{\pi }\int_0^{\pi }\frac {dz}{dx}\) cosn∅ d∅ | |
| 5. |
For γ(θ)=2V∞(A0\(\frac {1+cos\theta }{sin\theta }\) + Σ\(_{n=1}^∞\)sin nθ An) select the statement which is invalid. |
| A. | The solution is valid only for cambered airfoils |
| B. | The solution is valid for all thin airfoils |
| C. | A0 Is the n=0th term for the Fourier series |
| D. | Kutta condition is satisfied at the trailing edge i.e. θ=π. |
| Answer» B. The solution is valid for all thin airfoils | |
| 6. |
Select the statement which is not true for the solution of \(\frac {1}{2\pi } \int_0^c \frac {\gamma(\xi)d\xi}{x-\xi}\)=V∞(α-\(\frac {dz}{dx}\)) for a cambered airfoil. |
| A. | An depends on chord length of the airfoil |
| B. | A0 depends on the slope of the camber line |
| C. | An depends on the slope of the camber line |
| D. | A0 depends on the angle of attack |
| Answer» B. A0 depends on the slope of the camber line | |
| 7. |
For an angle of attack of 5° and slope of camber line being zero, find the value of A0. |
| A. | 0.087 |
| B. | 5 |
| C. | 0 |
| D. | -5 |
| Answer» B. 5 | |
| 8. |
NACA 0023 is______ |
| A. | Negatively cambered airfoil |
| B. | Positively cambered airfoil |
| C. | Symmetrical airfoil |
| D. | Thin cambered airfoil |
| Answer» D. Thin cambered airfoil | |
| 9. |
For NACA4313 what is the maximum camber and the position of maximum camber from the leading edge respectively is______ |
| A. | 0.04c, 0.4c |
| B. | 0.4c, 0.03c |
| C. | 0.13c, 0.4c |
| D. | 0.04c, 0.03c |
| Answer» B. 0.4c, 0.03c | |
| 10. |
The extra term appearing in the thin airfoil theory solution for a cambered airfoil is a______ |
| A. | Full Fourier series |
| B. | Fourier sine series |
| C. | Fourier cosine series |
| D. | Constant |
| Answer» C. Fourier cosine series | |
| 11. |
The equation \(\frac {1}{2\pi } \int_0^c \frac {\gamma(\xi)d\xi}{x-\xi}\)=V∞α is called the fundamental equation of thin airfoil theory for______ |
| A. | Cambered airfoils only |
| B. | Symmetric airfoils only |
| C. | All thin airfoils |
| D. | Symmetric and positively cambered airfoils |
| Answer» C. All thin airfoils | |
| 12. |
Which of the following is incorrect for a thin, cambered airfoil? |
| A. | The angle of attack is small |
| B. | The induced velocity distribution for the camber line is the same for the chord line |
| C. | Vortex sheet is kept at the chord line |
| D. | The slope of the camber line is zero |
| Answer» E. | |
| 13. |
The camber line is not a streamline of flow for a cambered airfoil according to the thin airfoil theory. |
| A. | Always true |
| B. | Always false |
| C. | True only for thin airfoils |
| D. | Depends on the camber distribution |
| Answer» C. True only for thin airfoils | |