GATE AE Airfoils and Wings PYQs & Answers

Questions 1–10 of 39. Imported answers require independent review unless marked reviewed.

The fundamental purpose of the Kutta condition in the thin airfoil theory is ________.

Your answerChoose one option.

to determine the total strength of the source distribution

to determine the speed of the uniform flow

to incorporate the essential effect of viscosity in the potential flow theory

to incorporate the concept of induced drag in the inviscid theory

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Shown below are qualitative illustrations of the lift curve for an airfoil when two different control surfaces are in their respective retracted and deployed configurations. Which of the following is/are TRUE?

Diagram for Aerospace Engineering question 25

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

Figure P is for a flap

Figure P is for a slat

Figure Q is for a slat

Figure Q is for a flap

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Which of the following statements is/are TRUE regarding critical and drag divergence Mach numbers of a wing?

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

Critical Mach number is the minimum freestream Mach number for which sonic condition is attained somewhere over the wing

Drag divergence Mach number is always higher than the critical Mach number

Drag divergence Mach number is the local Mach number over the wing at which the drag increases drastically

Critical Mach number is independent of the angle of attack

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An elliptic wing has a span of 6 m and a planform area of 6 m

. When generating a lift coefficient of 0.6, the induced drag it incurs is ________

(rounded off to 1 decimal place).

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What is/are the use(s) of the single horseshoe vortex model of finite wing aerodynamic theory?

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

It can approximate the wing pitching moment coefficient

It can approximate the wing induced drag coefficient

It can approximate the effect of the wing on the induced drag coefficient of a typical horizontal tail

It can approximate the aerodynamic benefit/penalty of formation flight compared to isolated flight

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For an airfoil section the pitch moment coefficient is determined about a reference point that is 0.3 times the chord behind the leading edge. It varies with the lift coefficient as shown in the table below. The distance of the aerodynamic center from the leading edge of the airfoil as a fraction of the chord is ________ (rounded off to one decimal place).

	0.2	0.4	0.6	0.8
	−0.02	0	0.02	0.04

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Consider a finite wing of aspect ratio 10 with span effectiveness factor 0.95. Its airfoil section has a lift slope of 0.106 per degree and a zero-lift angle of attack of −1.5°. The lift coefficient of the wing at an angle of attack of 3.5° is ________ (rounded off to 2 decimal places).

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Thin airfoil theory predicts the zero-lift angle of attack

of NACA 2412 airfoil as

. The corresponding prediction of

for NACA 5410 airfoil is ________ degrees (rounded off to 1 decimal place).

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For a NACA 4415 airfoil, the location of maximum camber, as a fraction of the chord length from the leading edge, is _____.

Your answerChoose one option.

0.44

0.40

0.15

0.04

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A positively cambered airfoil is placed in a uniform flow (velocity,

) at its zero-lift angle of attack. M is the corresponding pitching moment. Which one of the following representations accurately describes this scenario?

Your answerChoose one option.