MCQOPTIONS
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MCQOPTIONS
This section includes 10 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≤ ≤ |
| B. | ( frac {dz}{dx} )=0 |
| C. | = ( frac {c}{2} )(1-cos ) |
| D. | ( )=0 |
| Answer» E. | |
| 2. |
The Kutta Condition according to the thin airfoil theory is_____ |
| A. | (c)=0 |
| B. | (x)=0 |
| C. | ( )=0 |
| D. | ( frac {dz}{dx} )=0 |
| Answer» B. (x)=0 | |
| 3. |
The value of integral (_0^? frac {cos n theta d theta }{cos theta-cos } )= ( frac {sin n }{sin } ) is valid for the limit 0 to_____ |
| A. | |
| B. | 2 |
| C. | |
| D. | n |
| Answer» B. 2 | |
| 4. |
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. | |
| 5. |
The following equation is known as_________
|
| A. | n(Where c is the chord length for a thin airfoil, is the angle of attack, V<sub> </sub> is the free-stream velocity, ( frac {dz}{dx} ) is the slope at point x and (x) is the vortex strength at x). |
| B. | Airfoil equation |
| C. | The fundamental equation for airfoils |
| D. | The fundamental equation for symmetric airfoils |
| E. | The fundamental equation for thin airfoil theory |
| Answer» E. The fundamental equation for thin airfoil theory | |
| 6. |
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 | |
| 7. |
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 | |
| 8. |
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 . Then which of the following condition is true in case of thin airfoil theory? |
| A. | 15sin +4=0 |
| B. | 15+4=0 |
| C. | 15cos +4=0 |
| D. | 15tan -4=0 |
| Answer» C. 15cos +4=0 | |
| 9. |
What is the Kutta Condition in terms of strength ( ) of the thin airfoil? |
| A. | = 0 |
| B. | (LE) = 0 |
| C. | ( frac {D gamma }{Dt} )=0 |
| D. | (TE) = 0 |
| Answer» E. | |
| 10. |
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. | |