GATE AE Airfoils and Wings PYQs & Answers — Page 3

Questions 21–30 of 39. Imported answers require independent review unless marked reviewed.

NACA 2412 airfoil has

Your answerSelect all correct options. You can choose more than one.

4% maximum camber with respect to chord

maximum camber at 40% chord

12% maximum thickness to chord ratio

maximum camber at 20% chord

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Consider a circulation distribution over a finite wing given by the equation below.

The wingspan

is 10 m, the maximum circulation

is 20 m

/s, density of air is 1.2 kg/m

and the free stream speed is 80 m/s.

The lift over the wing is _____ N (rounded off to the nearest integer).

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Consider a thin symmetric airfoil at 2 degree angle of attack in a uniform flow at 50 m/s. The pitching moment coefficient about its leading edge is _____(rounded off to three decimal places).

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Which of the following statement(s) is/are true with regards to Kutta condition for flow past airfoils?

Your answerSelect all correct options. You can choose more than one.

It is utilized to determine the circulation on an airfoil.

It is applicable only to airfoils with sharp trailing edge.

The trailing edge of an airfoil is a stagnation point.

The flow leaves the trailing edge smoothly.

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According to the thin airfoil theory, which of the following statement(s) is/are true for a cambered airfoil?

Your answerSelect all correct options. You can choose more than one.

The lift coefficient for an airfoil is directly proportional to the absolute angle of attack.

The aerodynamic center lies at quarter chord point.

The center of pressure lies at quarter chord point.

Drag coefficient is proportional to the square of lift coefficient.

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A finite wing of elliptic planform with aspect ratio 10, whose section is a symmetric airfoil, is placed in a uniform flow at 5 degrees angle of attack. The induced drag coefficient for the wing is ______ (round off to three decimal places).

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Given access to the complete geometry, surface pressure and shear stress distribution over a body placed in a uniform flow, one can estimate

Your answerChoose one option.

the moment coefficient, and the force on the body.

the force coefficient, and the force on the body.

the moment coefficient, and the moment on the body.

the force and the moment on the body.

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The table shows the lift characteristics of an airfoil at low speeds. The maximum lift coefficient occurs at 16 degrees.

Angle of attack (in degrees)	Lift coefficient
0	0.10
4	0.53

Using Prandtl-Glauert rule, the lift coefficient for the airfoil at the angle of attack of 6 degrees and free stream Mach number of 0.6 is ______ (round off to two decimal places).

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A low speed uniform flow

is incident on an airfoil of chord

. In the figure, the velocity profile some distance downstream of the airfoil is idealized as shown for section B. The static pressure at sections A and B is the same. The drag coefficient of the airfoil is ______ (round off to three decimal places).

Diagram for Aerospace Engineering question 38

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A wing of 15 m span with elliptic lift distribution is generating a lift of 80 kN at a speed of 90 m/s. The density of surrounding air is 1.2 kg/m³. The induced angle of attack at this condition is ______ degrees (round off to two decimal places).

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GATE AE Airfoils and Wings PYQs

Question 26

Question 51

Question 54

Question 15

Question 16

Question 41

Question 5

Question 37

Question 38

Question 41