MCQOPTIONS
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MCQOPTIONS
This section includes 12 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
What leads to shear stress between the adjacent layers of fluid inside the boundary layer adjacent to the surface? |
| A. | Aerodynamics drag |
| B. | Viscosity |
| C. | Pressure drag |
| D. | Wave drag |
| Answer» C. Pressure drag | |
| 2. |
What is the equation for momentum thickness? |
| A. | <sup>*</sup> = ( int_0^ frac {u}{U_e} big [ )1 ( big ( frac {u}{U_e} big )^2 big ] )dy |
| B. | <sup>*</sup> = ( int_0^ frac {u}{U_e} big [ )1 ( frac {u}{U_e} big ] )dy |
| C. | <sup>*</sup> = ( int_0^ big [ )1 ( frac {u}{U_e} big ] )dy |
| D. | <sup>*</sup> = ( int_0^ frac {u}{U_e} big [ )1 + ( frac {u}{U_e} big ] )dy |
| Answer» C. <sup>*</sup> = ( int_0^ big [ )1 ( frac {u}{U_e} big ] )dy | |
| 3. |
What is the value of kinetic energy thickness? |
| A. | <sup>**</sup> = ( int_0^ frac {u}{U_e} big [ )1 ( big ( frac {u}{U_e} big )^2 big ] )dy |
| B. | <sup>**</sup> = ( int_0^ frac {u}{U_e} big [ )1 ( frac {u}{U_e} big ] )dy |
| C. | <sup>**</sup> = ( int_0^ big [ )1 ( frac {u}{U_e} big ] )dy |
| D. | <sup>**</sup> = ( int_0^ frac {u}{U_e} big [ )1 + ( frac {u}{U_e} big ] )dy |
| Answer» B. <sup>**</sup> = ( int_0^ frac {u}{U_e} big [ )1 ( frac {u}{U_e} big ] )dy | |
| 4. |
When the Reynolds number approaches infinity, what happens to the boundary layer thickness? |
| A. | Approaches infinity |
| B. | Approaches zero |
| C. | Approaches once |
| D. | Remains same |
| Answer» C. Approaches once | |
| 5. |
When there s flow over a flat plate, there s laminar boundary layer at the leading edge followed by turbulent boundary layer. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 6. |
According to the y momentum equation, how does the pressure vary inside the boundary layer normal in the direction normal to the surface? |
| A. | Increases |
| B. | Decreases |
| C. | Remains constant |
| D. | First increases then decreases |
| Answer» D. First increases then decreases | |
| 7. |
Which of these relations is applicable for turbulent and laminar boundary layer? |
| A. | <sub>T<sub>turbulent</sub></sub> < <sub>T<sub>laminar</sub></sub> |
| B. | <sub>T<sub>turbulent</sub></sub> = <sub>T<sub>laminar</sub></sub> |
| C. | <sub>turbulent</sub> < <sub>laminar</sub> |
| D. | <sub>turbulent</sub> > <sub>laminar</sub> |
| Answer» E. | |
| 8. |
The displacement thickness is the distance by which, due to the presence of the boundary layer, the flow streamline is displaced. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 9. |
In which case are the velocity and thermal boundary layer equal? |
| A. | Pr = 0 |
| B. | Pr = 1 |
| C. | Pr > 1 |
| D. | Pr < 1 |
| Answer» C. Pr > 1 | |
| 10. |
What is the thermal boundary layer? |
| A. | T = 0.90T<sub>e</sub> |
| B. | T = 0.89T<sub>e</sub> |
| C. | T = 0.99T<sub>e</sub> |
| D. | T = 0.97T<sub>e</sub> |
| Answer» D. T = 0.97T<sub>e</sub> | |
| 11. |
How is the boundary layer thickness defined? (ue is the outer edge velocity) |
| A. | u = 0.99u<sub>e</sub> |
| B. | u = 0.89u<sub>e</sub> |
| C. | u = 0.90u<sub>e</sub> |
| D. | u = 0.50u<sub>e</sub> |
| Answer» B. u = 0.89u<sub>e</sub> | |
| 12. |
Which of these is not a property of boundary layer? |
| A. | No slip condition at the surface |
| B. | Temperature of fluid at the surface is equal to wall temperature |
| C. | Flow velocity increases along y direction |
| D. | Thermal boundary layer is equal to velocity boundary layer |
| Answer» E. | |