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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. Pressure on the upper surface is _________
2. Which of the following is correct?
3. Which of these is not part of an airfoil?
4. An airfoil is operated with flow velocity such that the pressure on upper and lower surface are 30 Pa and 15 Pa respectively. If chord is 1m then, what will be the lift produced by this airfoil?
5. Camber represents the curvature of an airfoil.
6. A 3D airfoil is called _____________
7. Typically, high speed aircrafts have thinner tail as compared to wing thickness.
8. A jet fighter is operating at Mach number of 1.4. Wing chord is 1m then, find the location of aerodynamic centre.
9. The ratio of tip and root chord is called ____
10. Determine the corrections or otherwise of the following assertion [A] and reason [R]:
Assertion [A]: In general, wing twist should not be more than 6°.
Reason[R]: Wing twist is used to improve stall properties at tip.
11. An aerofoil is operating with flow velocity of 100m/s. Aerofoil is symmetric and is at 0° AOA. Determine lift produced by this aerofoil.
12. 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.
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. Which of the following is not an application of an airfoil?
15. If I want to locate my minimum pressure at 0.5 of chord c then _____________
16. Airfoil is a streamline shape.
17. 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.
18. 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.
19. What is the function of wing twist?
20. Which of the following is correct in accordance to diagram?
Let’s consider an aircraft has statistically determined aspect ratio of 8.1. Aircraft has canard which gives contribution of 10% for total lift. Determine the aspect ratio of wing."
21. What will be the location of maximum camber for NACA 13250 with chord length of 2m?
22. A NACA 22104 airfoil is operating at AOA = 3°. The lift-coefficient at this AOA is 0.15. Determine the value of angle of attack at designed lift co-efficient.
23. What is represented by ‘?’ in following diagram of an airfoil?
From following diagram body-1 is not streamline?
"NACA stands for _____"
24. The straight line joining L.E. and T.E. of an airfoil is _______
25. For high aspect ratio strength of the wing tip vortex is low.

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