MCQOPTIONS
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MCQOPTIONS
This section includes 25 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
Cl vs Cd is called as _______________ |
| A. | drag polar |
| B. | parasitic drag |
| C. | total drag |
| D. | no significance |
| Answer» B. parasitic drag | |
| 2. |
The shape of the wing is called as ____________ |
| A. | geometry |
| B. | wing |
| C. | airfoil |
| D. | wing box |
| Answer» D. wing box | |
| 3. |
In a wing, the coefficient of pressure at the upper surface is greater than the lower surface. |
| A. | true |
| B. | false |
| Answer» C. | |
| 4. |
Which of the following is an example of hydrostatic manometer? |
| A. | pressure gauge |
| B. | piston type gauge |
| C. | mercury column manometer |
| D. | spring manometer |
| Answer» D. spring manometer | |
| 5. |
Generally, the gliders have Cp as ________ |
| A. | 1 |
| B. | -1 |
| C. | 0 |
| D. | infinity |
| Answer» C. 0 | |
| 6. |
If the value of Cp=1, then the local pressure can be given as ___________ |
| A. | P = Pfreestream + q |
| B. | P = 0.5*ρ*V12 |
| C. | P = Pfreestream |
| D. | P = 0 |
| Answer» B. P = 0.5*ρ*V12 | |
| 7. |
The value of Cp for compressible flow can be given as ___________ |
| A. | Cp = P2-P1 |
| B. | Cp = 0 |
| C. | Cp = (P2-P1) /q |
| D. | Cp = 0.5*ρ*V12 |
| Answer» E. | |
| 8. |
For compressible flow, the value of Cp at stagnation point is __________ |
| A. | 0 |
| B. | negative |
| C. | infinity |
| D. | greater than 1 |
| Answer» E. | |
| 9. |
The highest value of Cp is given at ________ |
| A. | end points |
| B. | stagnation point |
| C. | everywhere in the flow field |
| D. | at boundaries |
| Answer» C. everywhere in the flow field | |
| 10. |
For incompressible flow, Cp is expressed only in terms of ____________ |
| A. | pressure |
| B. | density |
| C. | temperature |
| D. | velocity |
| Answer» E. | |
| 11. |
IN_A_WING,_THE_COEFFICIENT_OF_PRESSURE_AT_THE_UPPER_SURFACE_IS_GREATER_THAN_THE_LOWER_SURFACE.?$ |
| A. | true |
| B. | false |
| Answer» C. | |
| 12. |
WHICH_OF_THE_FOLLOWING_IS_AN_EXAMPLE_OF_HYDROSTATIC_MANOMETER??$ |
| A. | pressure gauge |
| B. | piston type gauge |
| C. | mercury column manometer |
| D. | spring manometer |
| Answer» D. spring manometer | |
| 13. |
Cl vs Cd is called as _______________$ |
| A. | drag polar |
| B. | parasitic drag |
| C. | total drag |
| D. | no significance |
| Answer» B. parasitic drag | |
| 14. |
The shape of the wing is called as ____________$ |
| A. | geometry |
| B. | wing |
| C. | airfoil |
| D. | wing box |
| Answer» D. wing box | |
| 15. |
The pressure and temperature are ________ |
| A. | directly proportional to each other |
| B. | inversely proportional to each other |
| C. | equal |
| D. | independent of each other |
| Answer» B. inversely proportional to each other | |
| 16. |
Pressure is _____ proportional to altitude. |
| A. | inversely |
| B. | directly |
| C. | no relation |
| D. | equal |
| Answer» B. directly | |
| 17. |
The aspect ratio (AR) is given by __________ |
| A. | b/s |
| B. | s/b |
| C. | b<sup>2</sup>/s |
| D. | s<sup>3</sup>/b |
| Answer» D. s<sup>3</sup>/b | |
| 18. |
Generally, the gliders have Cp as _______? |
| A. | 1 |
| B. | -1 |
| C. | 0 |
| D. | infinity |
| Answer» C. 0 | |
| 19. |
Ram is working on an experiment. He has a beaker in which fluid is moving at a very high velocity. He wants to calculate the relative pressure at each and every point of the flow. Which of the following will help him to do so? |
| A. | Coefficient of lift |
| B. | Coefficient of pressure |
| C. | Drag polar |
| D. | Velocity |
| Answer» C. Drag polar | |
| 20. |
If the value of Cp=1, then the local pressure can be given as ___________ |
| A. | P = P<sub>freestream</sub> + q |
| B. | P = 0.5*ρ*V<sub>1</sub><sup>2</sup> |
| C. | P = P<sub>freestream</sub> |
| D. | P = 0 |
| Answer» B. P = 0.5*‚âà√¨‚àö√ñ*V<sub>1</sub><sup>2</sup> | |
| 21. |
The value of Cp for compressible flow can be given as ___________ |
| A. | C<sub>p</sub> = P<sub>2</sub>-P<sub>1</sub> |
| B. | C<sub>p</sub> = 0 |
| C. | C<sub>p</sub> = (P<sub>2</sub>-P<sub>1</sub>) /q |
| D. | C<sub>p</sub> = 0.5*ρ*V<sub>1</sub><sup>2</sup> |
| Answer» E. | |
| 22. |
For compressible flow, the value of Cp at stagnation point is __________ |
| A. | 0 |
| B. | negative |
| C. | infinity |
| D. | greater than 1 |
| Answer» E. | |
| 23. |
The highest value of Cp is given at ________ |
| A. | end points |
| B. | stagnation point |
| C. | everywhere in the flow field |
| D. | at boundaries |
| Answer» C. everywhere in the flow field | |
| 24. |
For incompressible flow, Cp is expressed only in terms of ____________ |
| A. | pressure |
| B. | density |
| C. | temperature |
| D. | velocity |
| Answer» E. | |
| 25. |
Coefficient of pressure is a ________ |
| A. | dimensional quantity |
| B. | dimensionless quantity |
| C. | negligible value |
| D. | cannot be determined |
| Answer» C. negligible value | |