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 drag is prominent after exceeding the critical Mach number? |
| A. | Form drag |
| B. | Wave drag |
| C. | Pressure drag |
| D. | Skin friction drag |
| Answer» D. Skin friction drag | |
| 2. |
What happens to the flow around the airfoil at upper critical Mach number? |
| A. | The flow around airfoil becomes subsonic |
| B. | The flow around airfoil becomes supersonic |
| C. | The flow around airfoil becomes sonic |
| D. | The flow around airfoil becomes hypersonic |
| Answer» C. The flow around airfoil becomes sonic | |
| 3. |
Which equation is used to compute the critical Mach number of the airfoil? |
| A. | (C<sub>p</sub>)<sub>crit</sub> = ( frac {2}{ M_{crit}^{2}} bigg [ frac {1 + frac {1}{2}( 1)M_{crit}^{2}}{1 + frac {1}{2}( 1)} bigg ]^{ frac { }{ 1}} ) 1 |
| B. | (C<sub>p</sub>)<sub>crit</sub> = ( frac {2}{ M_{crit}^{2}} bigg [ frac {1 + frac {1}{2}( 1)M_{crit}^{2}}{1 + frac {1}{2}( 1)} bigg ]^{ frac { }{ + 1}} ) + 1 |
| C. | (C<sub>p</sub>)<sub>crit</sub> = M (_{crit}^{2} bigg [ frac {1 + frac {1}{2}( 1)}{1 + frac {1}{2}( 1)} bigg ]^{ frac { }{ 1}} ) 1 |
| D. | (C<sub>p</sub>)<sub>crit</sub> = M (_{crit}^{2} bigg [ frac {1 + frac {1}{2}( 1)}{1 + frac {1}{2}( 1)M_{crit}^{2}} bigg ]^{ frac { }{ 1}} ) 1 |
| Answer» B. (C<sub>p</sub>)<sub>crit</sub> = ( frac {2}{ M_{crit}^{2}} bigg [ frac {1 + frac {1}{2}( 1)M_{crit}^{2}}{1 + frac {1}{2}( 1)} bigg ]^{ frac { }{ + 1}} ) + 1 | |
| 4. |
Which of these techniques is employed to delay the critical Mach number? |
| A. | Increasing the thickness of airfoil |
| B. | Swept wing |
| C. | Increase camber |
| D. | Decrease drag divergence Mach number |
| Answer» C. Increase camber | |
| 5. |
What is the relation between the drag divergence Mach number and critical Mach number? |
| A. | M<sub>drag divergence</sub> = M<sub>crit</sub> |
| B. | M<sub>drag divergence</sub> > M<sub>crit</sub> |
| C. | M<sub>drag divergence</sub> < M<sub>crit</sub> |
| D. | M<sub>drag divergence</sub> M<sub>crit</sub> = 0 |
| Answer» C. M<sub>drag divergence</sub> < M<sub>crit</sub> | |
| 6. |
Thicker the airfoil, higher is the critical Mach number. |
| A. | True |
| B. | False |
| Answer» C. | |
| 7. |
What is the coefficient of pressure at minimum pressure point a function of? |
| A. | Critical Mach number |
| B. | Freestream Mach number |
| C. | Chord/thickness ratio of airfoil |
| D. | Length of the airfoil |
| Answer» B. Freestream Mach number | |
| 8. |
What is the coefficient of pressure at the minimum pressure point for an airfoil with critical Mach number as 0.6? |
| A. | 1.53 |
| B. | 1.66 |
| C. | 1.42 |
| D. | 1.15 |
| Answer» C. 1.42 | |
| 9. |
The local Mach number at a point on the airfoil reaches 1 for critical Mach number. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 10. |
What is a critical Mach number? |
| A. | Freestream Mach number for which stagnation pressure is obtained |
| B. | Freestream Mach number for which sonic flow is obtained |
| C. | Free stream Mach number for which supersonic flow is obtained |
| D. | Freestream Mach number for which hypersonic flow is obtained |
| Answer» C. Free stream Mach number for which supersonic flow is obtained | |