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. | δ* = \(\int_0^∞ \frac {u}{U_e} \big [ \)1 – \(\big ( \frac {u}{U_e} \big )^2 \big ] \)dy |
| B. | δ* = \(\int_0^∞ \frac {u}{U_e} \big [ \)1 – \(\frac {u}{U_e}\big ] \)dy |
| C. | δ* = \(\int_0^∞ \big [ \)1 – \(\frac {u}{U_e} \big ] \)dy |
| D. | δ* = \(\int_0^∞ \frac {u}{U_e} \big [ \)1 + \(\frac {u}{U_e} \big ]\)dy |
| Answer» C. δ* = \(\int_0^∞ \big [ \)1 – \(\frac {u}{U_e} \big ] \)dy | |
| 3. |
What is the value of kinetic energy thickness? |
| A. | δ** = \(\int_0^∞ \frac {u}{U_e}\big [ \)1 – \(\big ( \frac {u}{U_e}\big )^2 \big ] \)dy |
| B. | δ** = \(\int_0^∞ \frac {u}{U_e} \big [ \)1 – \(\frac {u}{U_e}\big ] \)dy |
| C. | δ** = \(\int_0^∞ \big [ \)1 – \(\frac {u}{U_e} \big ] \)dy |
| D. | δ** = \(\int_0^∞ \frac {u}{U_e} \big [ \)1 + \(\frac {u}{U_e}\big ] \)dy |
| Answer» B. δ** = \(\int_0^∞ \frac {u}{U_e} \big [ \)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. | δTturbulent < δTlaminar |
| B. | δTturbulent = δTlaminar |
| C. | δturbulent < δlaminar |
| D. | δturbulent > δlaminar |
| 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 = 0.90Te |
| B. | T = 0.89Te |
| C. | T = 0.99Te |
| D. | T = 0.97Te |
| Answer» D. T = 0.97Te | |
| 11. |
How is the boundary layer thickness defined? (ue is the outer edge velocity) |
| A. | u = 0.99ue |
| B. | u = 0.89ue |
| C. | u = 0.90ue |
| D. | u = 0.50ue |
| Answer» B. u = 0.89ue | |
| 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. | |