GATE AE topic:aerospace-engineering PYQs & Answers — Page 44

Questions 431–440 of 650. Imported answers require independent review unless marked reviewed.

For three different airplanes A, B and C, the yawing moment coefficient (

) was measured in a wind-tunnel for three settings of sideslip angle

and tabulated as:

Sideslip angle	Airplane A	Airplane B	Airplane C
deg	-0.030	-0.025	0.040
deg	0	0	0
deg	0.030	0.025	-0.040

Which one of the following statements is true regarding directional static stability of the airplanes A, B and C?

Your answerChoose one option.

All three airplanes A, B and C are stable.

Only airplane C is stable, while both A and B are unstable.

Airplane C is unstable, A and B are stable with A being more stable than B.

Airplane C is unstable, A and B are both stable with A less stable than B.

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A closed curve is expressed in parametric form as

and

, where

m and

m. Approximating

, which of the following is the area enclosed by the curve?

Your answerChoose one option.

110 m²

74 m²

35 m²

144 m²

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An axial compressor is designed to operate at a rotor speed of 1500 rpm and an inlet station temperature of 300 K. During compressor testing, the inlet station temperature of the compressor measured was 280 K. What should be the rotor speed for the compressor to develop the same performance characteristics during this test as in the design condition?

Your answerChoose one option.

1400 rpm

1449 rpm

1526 rpm

1607 rpm

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For the state of stress shown in the figure, which one of the following represents the correct free body diagram showing the maximum shear stress and the associated normal stresses?

Diagram for Aerospace Engineering question 34

Your answerChoose one option.

Diagram for Aerospace Engineering question 34 (figure 2)

Diagram for Aerospace Engineering question 34 (figure 3)

Diagram for Aerospace Engineering question 34 (figure 4)

Diagram for Aerospace Engineering question 34 (figure 5)

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In the equation

, where

is an orthogonal matrix, the sum of the unknowns,

______ (round off to one decimal place).

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is evaluated numerically using trapezoid rule with four intervals, the difference between the numerically evaluated value and the analytical value of the integral is equal to ______ (round off to three decimal places).

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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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An oblique shock is inclined at an angle of 35 degrees to the upstream flow of velocity 517.56 m/s. The deflection of the flow due to this shock is 5.75 degrees and the temperature downstream is 182.46 K. Assume the gas constant

J/(kg K), specific heat ratio

, and specific heat at constant pressure

J/(kg K). Using conservation relations, the Mach number of the upstream flow can be obtained as ______ (round off to one decimal place).

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The thickness of a laminar boundary layer (

) over a flat plate is

, where

is measured from the leading edge along the length of the plate. The velocity profile within the boundary layer is idealized as varying linearly with

. For freestream velocity of 3 m/s and kinematic viscosity of

m²/s, the displacement thickness at 0.5 m from the leading edge is ______ mm (round off to two decimal places).

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GATE AE topic:aerospace-engineering PYQs

Question 31

Question 32

Question 33

Question 34

Question 35

Question 36

Question 37

Question 38

Question 39

Question 40