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. |
Which of the following is not correct for symmetric airfoil according to the fundamental equation of thin airfoil in transformed coordinates? |
| A. | 0≤θ≤π |
| B. | \(\frac {dz}{dx}\)=0 |
| C. | ξ=\(\frac {c}{2}\)(1-cosθ) |
| D. | γ(θ)=0 |
| Answer» E. | |
| 2. |
The Kutta Condition according to the thin airfoil theory is_____ |
| A. | γ(c)=0 |
| B. | γ(x)=0 |
| C. | |
| Answer» B. γ(x)=0 | |
| 3. |
The value of integral ∫\(_0^?\frac {cosn\theta d\theta }{cos\theta-cos∅}\)=π\(\frac {sin n∅}{sin ∅}\) is valid for the limit 0 to_____ |
| A. | π |
| B. | 2π |
| C. | –π |
| D. | nπ |
| Answer» B. 2π | |
| 4. |
Identify ‘a’ as shown in the figure for a thin airfoil. |
| A. | Camber |
| B. | Chord Line |
| C. | Camber and Chord Line |
| D. | Neither Chord Line neither Camber |
| Answer» D. Neither Chord Line neither Camber | |
| 5. |
The fundamental equation for the thin airfoil theory does not encompass which of the following approximations? |
| A. | The angle of attack and slope of the camber line is small |
| B. | Camber line induced velocity distribution is the same for chord line |
| C. | Vortex sheet is placed at the chord line |
| D. | Kutta condition is satisfied at the trailing edge |
| Answer» E. | |
| 6. |
The following equation is known as_________Equation: \(\frac {1}{2\pi }\int_0^c \frac {\gamma (\xi)d\xi }{(x-\xi)}\)=V∞(α-\(\frac {dz}{dx}\))(Where c is the chord length for a thin airfoil, α is the angle of attack, V∞ is the free-stream velocity, \(\frac {dz}{dx}\) is the slope at point x and γ(x) is the vortex strength at x). |
| A. | Airfoil equation |
| B. | The fundamental equation for airfoils |
| C. | The fundamental equation for symmetric airfoils |
| D. | The fundamental equation for thin airfoil theory |
| Answer» E. | |
| 7. |
Which is the component of free-stream velocity normal to the camber line for the given thin airfoil? |
| A. | i |
| B. | iii |
| C. | ii |
| D. | V∞ |
| Answer» D. V∞ | |
| 8. |
Find the induced velocity in the direction normal to the camber line a point on where the slope is 0.087. Given the angle of attack is 5° and free-stream velocity is 20 units. Use thin airfoil approximation. |
| A. | 0 |
| B. | 101.74 units |
| C. | 98.26 units |
| D. | 3.48 units |
| Answer» B. 101.74 units | |
| 9. |
Identify the missing angle given by the question mark for the following camber distribution of a thin airfoil. |
| A. | tan-1α |
| B. | tan-1-\(\frac {dz}{dx}\) |
| C. | tan-1\(\frac {dz}{dx}\) |
| D. | tan-1–\(\frac {dz}{dx}\)+α |
| Answer» C. tan-1\(\frac {dz}{dx}\) | |
| 10. |
The thin airfoil theory assumes the vortex sheet is kept along the chord line and the camber line acts as a__________ |
| A. | Streamline |
| B. | Vortex Filament |
| C. | Another Vortex Sheet |
| D. | Dividing Streamline |
| Answer» B. Vortex Filament | |
| 11. |
Given the component of free-stream velocity in the direction perpendicular to the camber line is 15 units and the velocity induced by the vortex sheet is 4 units at a point. The angle of attack for the thin airfoil is α. Then which of the following condition is true in case of thin airfoil theory? |
| A. | 15sinα+4=0 |
| B. | 15+4=0 |
| C. | 15cosα+4=0 |
| D. | 15tanα-4=0 |
| Answer» C. 15cosα+4=0 | |
| 12. |
What is the Kutta Condition in terms of strength (γ) of the thin airfoil? |
| A. | γ = 0 |
| B. | γ(LE) = 0 |
| C. | \(\frac {D\gamma }{Dt}\)=0 |
| D. | γ(TE) = 0 |
| Answer» E. | |
| 13. |
A vortex sheet placed along the chord line gives the best representation for______ |
| A. | Thick Airfoil |
| B. | NACA Airfoils |
| C. | Negatively Cambered Airfoil |
| D. | Thin Airfoil |
| Answer» E. | |