GATE AE discipline:aerospace-engineering PYQs & Answers — Page 9

Questions 81–90 of 650. Imported answers require independent review unless marked reviewed.

______.

Your answerChoose one option.

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For a two-dimensional incompressible flow over a flat plate, the laminar boundary layer thickness at a distance

from the leading edge is

. If

is the Reynolds number defined based on length scale

is proportional to _____.

Your answerChoose one option.

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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.

Diagram for Aerospace Engineering question 19

Diagram for Aerospace Engineering question 19 (figure 2)

Diagram for Aerospace Engineering question 19 (figure 3)

Diagram for Aerospace Engineering question 19 (figure 4)

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Consider a pair of point vortices with clockwise circulation

each. The distance between their centers is

, as shown in the figure. Assume two-dimensional, incompressible, inviscid flow. Which one of the following options is correct?

Diagram for Aerospace Engineering question 20

Your answerChoose one option.

The vortices translate downwards together with a velocity

The vortices translate upwards together with a velocity

The vortices rotate clockwise around each other about their centroid O.

The vortices rotate counter-clockwise around each other about their centroid O.

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In a fluid flow, Mach number is an estimate of _____.

Your answerChoose one option.

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A general aviation airplane is in steady and level flight. The airplane is prone to adverse yaw. Which one of the following options best describes the deflections of aileron and rudder to achieve a coordinated right turn?

Your answerChoose one option.

Left aileron: down; Right aileron: up; Rudder: left

Left aileron: down; Right aileron: up; Rudder: right

Left aileron: up; Right aileron: down; Rudder: left

Left aileron: up; Right aileron: down; Rudder: right

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For a general aviation airplane, which one of the following has a destabilizing effect on its static roll stability?

Your answerChoose one option.

Wing with a positive dihedral angle

Fuselage with a high wing

Fuselage with a low wing

Swept back wing

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A general aviation airplane is flying at an altitude of 5000 m. The indicated airspeed is 250 km/h. Assume that there are no instrument errors and position errors. Neglecting compressibility effects, which one of the following options is FALSE?

Your answerChoose one option.

The true airspeed is greater than 250 km/h.

The calibrated airspeed is 250 km/h.

The true airspeed is 250 km/h.

The equivalent airspeed is 250 km/h.

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To achieve longitudinal static stability of a general aviation airplane, which one of the following conditions should be satisfied?

Your answerChoose one option.

The center of gravity of the airplane should be aft of the neutral point.

The center of gravity of the airplane should be forward of the neutral point.

The stability coefficient

(

is the airplane pitching moment coefficient and

is the angle of attack) is positive.

The static margin is negative.

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GATE AE discipline:aerospace-engineering PYQs

Question 16

Question 17

Question 18

Question 19

Question 20

Question 21

Question 22

Question 23

Question 24

Question 25