MCQOPTIONS
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MCQOPTIONS
This section includes 7 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
Mach number independence for conical cylinder is achieved at a lower Mach number compared to the sphere. |
| A. | True |
| B. | False |
| Answer» C. | |
| 2. |
What happens to the pressure behind an oblique shock wave at very high Mach numbers? |
| A. | <sub>2</sub> = ( frac {2sin^2 }{ + 1} ) |
| B. | <sub>2</sub> = ( frac { 1}{ + 1} ) |
| C. | <sub>2</sub> = 1 ( frac {2sin^2 }{ + 1} ) |
| D. | <sub>2</sub> = ( frac {2sin 2 }{ + 1} ) |
| Answer» B. <sub>2</sub> = ( frac { 1}{ + 1} ) | |
| 3. |
For a flow with Mach number 4, P1 = 2.65 104 Pa what is the pressure behind the oblique shock wave having shock angle as 30 degrees? |
| A. | 8.525 10<sup>4</sup> Pa |
| B. | 11.925 10<sup>4</sup> Pa |
| C. | 4.502 10<sup>4</sup> Pa |
| D. | 15.278 10<sup>4</sup> Pa |
| Answer» C. 4.502 10<sup>4</sup> Pa | |
| 4. |
Boundary condition V.n = 0 is applied at the surface to non dimensionlize the governing equations when fluid is being transferred. |
| A. | True |
| B. | False |
| Answer» C. | |
| 5. |
Which boundary condition applied at the surface to non dimensionlize the governing equations? |
| A. | <b>V</b>.n = 0 |
| B. | <b>V</b> n = 0 |
| C. | <b>V</b>.(<b>V</b> n) = 0 |
| D. | <b>V</b> (<b>V</b> n) = 0 |
| Answer» B. <b>V</b> n = 0 | |
| 6. |
Which of these equations represents non dimensionalize continuity equation? |
| A. | ( frac {( overline { } , overline {u})}{ overline {x}} ) + ( frac {( overline { } , overline {v})}{ overline {y}} ) + ( frac {( overline { } , overline {w})}{ overline {z}} ) = 0 |
| B. | ( frac { overline {u}}{ overline {x}} ) + ( frac { overline {v}}{ overline {y}} ) + ( frac { overline {w}}{ overline {z}} ) = 0 |
| C. | ( frac { overline {u}}{ overline {x}} ) + ( frac { overline {v}}{ overline {y}} ) + ( frac { overline {w}}{ overline {z}} ) = ( frac { overline {p}}{ overline {x}} ) |
| D. | ( frac { overline {u}}{ overline {x}} ) + ( frac { overline {v}}{ overline {y}} ) + ( frac { overline {w}}{ overline {z}} ) = ( frac { overline {p}}{ y} ) |
| Answer» B. ( frac { overline {u}}{ overline {x}} ) + ( frac { overline {v}}{ overline {y}} ) + ( frac { overline {w}}{ overline {z}} ) = 0 | |
| 7. |
At which flow regime does aerodynamic quantities such as coefficient of pressure, lift become independent of Mach number? |
| A. | Subsonic |
| B. | Supersonic |
| C. | Transonic |
| D. | Hypersonic |
| Answer» E. | |