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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. If a sailplane is to be designed then, the aspect ratio of the sailplane will be ______
2. We are using the airfoil in the aircraft as _____
3. Which of these is not part of an airfoil?
4. Which of the following is not an application of an airfoil?
5. 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.
6. The parameter marked by ’?’ in the diagram is _____
The cross-sectional shape of wing is called _____"
7. Pitching moment co-efficient for an airfoil is given by _____
8. Typically tail provides ______
9. Which control surface is primarily used for spin recovery?
10. Camber represents the curvature of an airfoil.
11. Which of the following is correct?
12. A wing has root chord of 2m and taper ratio of 0.5. Determine what will be the value of tip chord?
13. 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°.
14. If taper ratio is T and span is b with surface area as S then the root chord is _____
15. What will be the location of maximum camber for NACA 13250 with chord length of 2m?
16. An aerofoil is operating with flow velocity of 100m/s. Aerofoil is symmetric and is at 0° AOA. Determine lift produced by this aerofoil.
17. If I want to locate my minimum pressure at 0.5 of chord c then _____________
18. A twin turboprop engine is flying with 120m/s. Wing of the aircraft has span of 2m and lift co-efficient as 0.15 with aspect ratio as 9.2. Find the lift produced by the wing.
19. For a cambered airfoil section lift is 30N. Airfoil is operating in such way that dynamic lift is 20N. Determine the lift co-efficient for the airfoil.
20. Typically, high speed aircrafts have thinner tail as compared to wing thickness.
21. If aspect ratio of wing is 8 and S=0.1m2 then, what will be the span of wing?
22. Let’s consider we need to design supersonic aircraft then, which type of airfoil should be adopted?
23. An aircraft with elliptic wing planform has parasite drag coefficient as 0.9. Lift coefficient of wing is 1.8 and aspect ratio is 8.5. Find total drag coefficient for the wing.
24. If root chord is 2m and tip chord is 0.9m then, find taper ratio.
25. What is represented by ‘?’ in following diagram of an airfoil?
From following diagram body-1 is not streamline?
"NACA stands for _____"

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