MCQOPTIONS
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MCQOPTIONS
This section includes 40 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
The lower end of the pitot tube is bet at an angle of ____________ |
| A. | 120 degrees |
| B. | 360 degrees |
| C. | 90 degrees |
| D. | 45 degrees |
| Answer» D. 45 degrees | |
| 2. |
In a pitot tube, the kinetic energy is converted into _________ |
| A. | potential energy |
| B. | total energy |
| C. | pressure energy |
| D. | internal energy |
| Answer» D. internal energy | |
| 3. |
Pitot tube with flat faces are more sensitive. |
| A. | True |
| B. | False |
| Answer» C. | |
| 4. |
When the local flow velocity is zero itself then _________ |
| A. | total pressure is not equal to static pressure |
| B. | total pressure is equal to static pressure |
| C. | 0 |
| D. | infinity |
| Answer» C. 0 | |
| 5. |
An aircraft is flying at cruise level with a velocity of 110m/s at an altitude of 10 km and the dynamic pressure is 5.43kN/m2. Now assume the aircraft is flying is at sea level with a speed of 65m/s and the same dynamic pressure. In the above data, the velocity 65m/s refers to __________ |
| A. | true air speed |
| B. | equivalent airspeed |
| C. | free stream velocity |
| D. | cruising speed |
| Answer» C. free stream velocity | |
| 6. |
In a wing, the coefficient of pressure at the upper surface is greater than the lower surface. |
| A. | true |
| B. | false |
| Answer» C. | |
| 7. |
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 | |
| 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. |
For incompressible flow, Cp is expressed only in terms of ____________ |
| A. | pressure |
| B. | density |
| C. | temperature |
| D. | velocity |
| Answer» E. | |
| 10. |
Generally, the gliders have Cp as ________ |
| A. | 1 |
| B. | -1 |
| C. | 0 |
| D. | infinity |
| Answer» C. 0 | |
| 11. |
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 | |
| 12. |
If the value of Cp=1, then the local pressure can be given as ___________ |
| A. | P = Pfreestream + q |
| B. | P = 0.5*?*V12 |
| C. | P = Pfreestream |
| D. | P = 0 |
| Answer» B. P = 0.5*?*V12 | |
| 13. |
Inside a wind tunnel, the area further decreases from A2 to A3, that section is called as _______ |
| A. | Converging section |
| B. | Divergent section |
| C. | Throat section |
| D. | Nozzle |
| Answer» C. Throat section | |
| 14. |
The open circuit wind tunnel is similar to venturi duct ______ |
| A. | True |
| B. | False |
| Answer» B. False | |
| 15. |
The flows in which all the flow parameters are the function of 'x' is called as _________ |
| A. | 3D flow |
| B. | 2D flow |
| C. | Quasi 1D flow |
| D. | Quasi 2D flow |
| Answer» D. Quasi 2D flow | |
| 16. |
The shape of the wing is called as ____________ |
| A. | geometry |
| B. | wing |
| C. | airfoil |
| D. | wing box |
| Answer» D. wing box | |
| 17. |
Cl vs Cd is called as _______________ |
| A. | drag polar |
| B. | parasitic drag |
| C. | total drag |
| D. | no significance |
| Answer» B. parasitic drag | |
| 18. |
Two pathline can __________ |
| A. | intersect each other |
| B. | cannot intersect each other |
| C. | can meet at infinity |
| D. | cannot meet ever |
| Answer» B. cannot intersect each other | |
| 19. |
Consider a fixed point in a flow. The locus of all the point passed through this fixed point is called as _________ |
| A. | stream-line |
| B. | pathline |
| C. | streak lines |
| D. | stream tubes |
| Answer» D. stream tubes | |
| 20. |
The flow in which streamlines are directed away from the origin is called as __________ |
| A. | sink flow |
| B. | doublet flow |
| C. | source flow |
| D. | source-sink flow |
| Answer» D. source-sink flow | |
| 21. |
______ gives the velocity component at right angles to a particular direction. |
| A. | velocity |
| B. | velocity vector |
| C. | stream function |
| D. | pressure line |
| Answer» D. pressure line | |
| 22. |
Consider a flow over a flat plate of uniform cross section area, the flow moves at a constant speed. Due to a certain disturbance, there is a disturbance in the flow. In the given scenario, which of the following statement is true? |
| A. | The flow remains uniform even after the disturbance |
| B. | The flow remains uniform throughout |
| C. | The flow is the first uniform and after disturbance undergoes non-uniformity |
| D. | The disturbance will change the cross section area |
| Answer» D. The disturbance will change the cross section area | |
| 23. |
For an irrotational flow, the velocity component along z-direction becomes _________ |
| A. | 0 |
| B. | 1 |
| C. | infinity |
| D. | -1 |
| Answer» B. 1 | |
| 24. |
When velocity potential (?) exits, the flow is _________ |
| A. | rotational |
| B. | irrotational |
| C. | laminar |
| D. | turbulent |
| Answer» C. laminar | |
| 25. |
The units of viscosity are __________ |
| A. | N/m |
| B. | Ns/m2 |
| C. | m/s |
| D. | Dimension less quantity |
| Answer» C. m/s | |
| 26. |
When velocity potential (F) is constant, it is called as _________ |
| A. | velocity line |
| B. | velocity curve |
| C. | potential line |
| D. | equipotential line |
| Answer» E. | |
| 27. |
Density is ratio of __________ |
| A. | mass to volume |
| B. | volume to mass |
| C. | mass to pressure |
| D. | pressure to volume |
| Answer» B. volume to mass | |
| 28. |
A combination of uniform flow and doublet flow gives ______________ |
| A. | flow past a circular cylinder |
| B. | flow past a wedge |
| C. | flow past a plate |
| D. | flow over any body |
| Answer» B. flow past a wedge | |
| 29. |
What will be the shape of Rankine oval when sin ?=0? |
| A. | vertical line |
| B. | horizontal line |
| C. | a point |
| D. | curve |
| Answer» C. a point | |
| 30. |
Why the circular cylinder will create more drag? |
| A. | The pressure difference between upstream and downstream direction of flow |
| B. | The pressure difference between relative wind and downstream direction of flow |
| C. | The pressure difference between upstream and direction of flow |
| D. | The pressure difference between downstream of flow |
| Answer» B. The pressure difference between relative wind and downstream direction of flow | |
| 31. |
A body floats on the surface when ____________ |
| A. | metacenter is above gravity |
| B. | metacenter is below gravity |
| C. | metacenter is equal to gravity |
| D. | gravity is above metacenter |
| Answer» B. metacenter is below gravity | |
| 32. |
What is the position of stagnation point, when a cylinder is placed in the wind tunnel? |
| A. | Lower part |
| B. | Upper part |
| C. | Middle part |
| D. | No stagnation point |
| Answer» B. Upper part | |
| 33. |
How the finite lift is measured in the cylinder? |
| A. | Moving up and down |
| B. | Moving up |
| C. | Moving left and right |
| D. | Spinning cylinder |
| Answer» E. | |
| 34. |
What is the condition for rotational flow in Kutta-Joukowski theorem? |
| A. | Small number of unsteady flow |
| B. | Large number of unsteady flow |
| C. | Large number of steady flow |
| D. | Small number of steady flow |
| Answer» C. Large number of steady flow | |
| 35. |
Purpose of non-lifting flow over an arbitrary body is _____________ |
| A. | to find a numerical method |
| B. | to find a mathematical method |
| C. | to find a lifting body |
| D. | to find a drag body |
| Answer» B. to find a mathematical method | |
| 36. |
Is complete velocity potential at point 'p' is obtained by entire source sheet from a to b? |
| A. | True |
| B. | False |
| Answer» B. False | |
| 37. |
Is vector (v) is positive when directed away from the body? |
| A. | True |
| B. | False |
| Answer» B. False | |
| 38. |
How rotating flow is induced? |
| A. | Joint effect of airfoil |
| B. | Joint effect of chord |
| C. | Joint effect of camber |
| D. | Joint effect of camber line |
| Answer» D. Joint effect of camber line | |
| 39. |
Kutta-Joukowski theorem refers to __________ |
| A. | two-dimensional flow around an airfoil |
| B. | one-dimensional flow around an airfoil |
| C. | three-dimensional flow around an airfoil |
| D. | flows around an airfoil |
| Answer» B. one-dimensional flow around an airfoil | |
| 40. |
What is the normal component of the flow velocity at the rth control point? |
| A. | Sum of the freestream |
| B. | Sum of source line |
| C. | Sum of the sink line |
| D. | Sum of the source and sink line |
| Answer» B. Sum of source line | |