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Aerodynamics Practice Test: Flow over Airfoils over Finite Wing
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Avg score: 3% • Most missed: “The incorrect choice for the general lift distribution for a finite wing is ____…”
Flow over Airfoils over Finite Wing topics include: Downwash and induced drag, vortex filament, biot savart law, helmholtz theorem, prandtl’s classical lifting line and lifting surface theory. Flow over a finite wing is three-dimensional, while flow over an airfoil is two-dimensional. The flow tends to leak around the wing tips, creating a trailing vortex at each tip.  The flow over the wing creates a circulatory motion that trails downstream. This motion creates wing-tip vortices that induce a small downward component of air velocity. This downward component is called downwash. The... Show more
Aerodynamics Practice Test: Flow over Airfoils over Finite Wing
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25 Questions

1. Is lift over each wing segment is correspond?
2. Is vortex filament is a very thin strip?
3. Identify the correct expression for the induced velocity by a semi-infinite vortex filament at a point.
(Where symbols have their usual meaning)
4. The elliptical lift distribution has a major interest in making wings because_____
5. Is local induced change the angle of attack on a given section of a wing?
6. The correct formula for profile drag coefficient over the finite wing is_______
7. Is 2D version of Biot-Savart equation is used, when the sources are invariant in one direction?
8. Is Helmholtz’s theorems apply to inviscid flows?
9. The incorrect statement for a finite wing with elliptical lift distribution out of the following is_____
10. The induced angle of attack for an elliptical lift distribution increase when ______
11. Is induced drag produce lift?
12. For a finite wing, the local relative wind differs by the free-stream velocity by some angle. This angle is called as ____
13. Is air pressure on the top of the wing is lower than the pressure below the wing?
14. Having a different zero angle of attack along span-wise locations is termed as______
15. The values of lift slope for elliptic wing (ae) and general planform wing (a) is less than that for airfoil (a0).
Mark the false statement.
16. The circulation at the center for an elliptical wing distribution does not depend upon ________
17. Is down wash is change in direction of lift?
18. The downward velocity induced by the trailing vortex in the vicinity of the wing-tips is called as _____
19. The incorrect statement in relation to the fundamental equation of Prandtls lifting line theory is_____
20. Select the incorrect equation for the induced drag coefficient for a finite wing.
21. Select the incorrect statement regarding the terminology used in the study of incompressible flow over finite wings.
22. The span-wise component of flow over the top surface of the wing flows______
23. Induced drag is generated by a component of lift for a finite wing.
24. The trailing vortex increases the requirement of power by the aircraft engine.
25. Is strength of a vortex tube vary with time?

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