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Aircraft Design Practice Test: Airfoil and Geometry Selection
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Avg score: 25% • Most missed: “Determine the corrections or otherwise of the following assertion [A] and reason…”

This quiz covers: Airfoil selection, wing geometry, tail geometry and arrangement.

The shape of the airfoil is defined using the following geometrical parameters: The mean camber line or mean line is the locus of points midway between the upper and lower surfaces. Its shape depends on the thickness distribution along the chord; The thickness of an airfoil varies along the chord.

Aircraft Design Practice Test: Airfoil and Geometry Selection
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25 Questions

1. Glider with span of 2m is flying at 10000ft. If aspect ratio of tail is 10 then, determine reference area of the tail.
2. Determine the corrections or otherwise of the following assertion [A] and reason [R]:
Assertion [A]: Most of the airfoils are built with blunt trailing edge having very small finite thickness.
Reason[R]: Perfect sharp trailing edge is difficult to build.
3. Determine the corrections or otherwise of the following assertion [A] and reason [R]:
Assertion [A]: Most of the tails are using symmetric airfoils.
Reason[R]: Tail control has two primary control surface.
4. Determine the value for maximum camber for NACA1235 airfoil. Given chord is 1m.
5. Which of the following is correct?
6. Airfoil is a streamline shape.
7. Find location of aerodynamic centre from leading edge if, chord is 10m and airfoil has flow velocity of 0.2 M.
8. A 3D airfoil is called _____________
9. We are using the airfoil in the aircraft as _____
10. An airfoil with symmetric profile has pitching moment about aerodynamic centre as 13 Nm at 4° AOA. Determine Pitching moment at same point if AOA is increased by 8°.
11. The maximum lift co-efficient for NACA 19584 (chord=2.5m) airfoil is____
12. Wing aspect ratio is defined as _____
13. If root chord is 2m and tip chord is 0.9m then, find taper ratio.
14. Typically tail provides ______
15. If I want to locate my minimum pressure at 0.5 of chord c then _____________
16. Wing and airfoil both are 3D phenomena.
17. Determine the corrections or otherwise of the following assertion [A] and reason [R]:
Assertion [A]: Most of the wings are using cambered airfoils.
Reason[R]: Cambered airfoils can produce positive lift at 0° AOA.
18. Which of the following is not an application of an airfoil?
19. The straight line joining L.E. and T.E. of an airfoil is _______
20. A wing has root chord of 2m and taper ratio of 0.5. Determine what will be the value of tip chord?
21. If aspect ratio of wing is 8 and S=0.1m2 then, what will be the span of wing?
22. Why dorsal fins are used?
23. Pressure on the upper surface is _________
24. Which of these is not part of an airfoil?
25. Let’s consider we need to design supersonic aircraft then, which type of airfoil should be adopted?

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