GATE AE topic:aerospace-engineering PYQs & Answers — Page 32

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Questions 311–320 of 650. Imported answers require independent review unless marked reviewed.

Topic practice 650 questionsPage 32 of 65

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 solid cylinder housed inside another cylinder as shown in the figure. Radius of the inner cylinder is 1 m and its height is 2 m. The gap between the cylinders is 5 mm and is filled with a fluid of viscosity

Pa-s.

The inner cylinder is rotating at a constant angular speed of 5 rad/s while the outer cylinder is stationary. Friction at the bottom surfaces can be ignored. Velocity profile in the vertical gap between the cylinders can be assumed to be linear.

The driving moment required for the rotating motion of the inner cylinder is __________ Nm (rounded off to two decimal places).

Diagram for Aerospace Engineering question 52

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In a converging duct, area and velocity at section P are 1 m

and 15 m/s, respectively. The temperature of the fluid is 300 K.

Air flow through the nozzle can be assumed to be inviscid and isothermal. Characteristic gas constant is 287 J/(kg-K) and ratio of specific heats is 1.4 for air.

To ensure that the air flow remains incompressible (Mach number,

) in the duct, the minimum area required at section Q is ____ m

(rounded off to two decimal places).

Diagram for Aerospace Engineering question 53

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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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A convergent-divergent nozzle with adiabatic walls is designed for an exit Mach number of 2.3. It is discharging air to atmosphere under the conditions indicated in the figure.

Flow through the nozzle is inviscid, the characteristic gas constant for air is 287 J/(kg-K), and

When the reservoir pressure is 25 bar (absolute), and temperature is 300 K, Prandtl-Meyer expansion waves appear at the nozzle exit as shown.

The minimum percentage change in the reservoir pressure required to eliminate the wave system at the nozzle exit under steady state is ______ %.

Diagram for Aerospace Engineering question 55

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A conventional airplane of mass 500 kg is doing a level turn of radius 1000 m at a constant speed of 100 m/s at sea level.

Taking the acceleration due to gravity as 10 m/s

, the bank angle of the airplane is __________ degrees.

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Given: The tip deflection and tip slope for a tip loaded cantilever of length

are:

and

, respectively, where

is the tip force and

is the flexural rigidity.

A cantilever

of rectangular cross-section is subjected to transverse load,

, at its mid-point. Two cases are considered as shown in the figure. In Case I, the end

is free and in Case II,

is simply supported.

The ratio of the magnitude of the maximum bending stress at

in Case I to that in Case II is ______ (rounded off to one decimal place).

Diagram for Aerospace Engineering question 57

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A simply supported Aluminium column of length 1 m and rectangular cross-section

with

, is subjected to axial compressive loading.

Young’s modulus is 70 GPa. Yield stress under uniaxial compression is 120 MPa.

The value of

at which the failure load for yielding and buckling coincide is ______ mm.

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A 0.5 m long thin-walled circular shaft of radius 2 cm is to be designed for an axial load of 7.4 kN and a torque of 148 Nm applied at its tip, as shown in the figure.

The allowable stress under uniaxial tension is 100 MPa.

Using maximum principal stress criterion, the minimum thickness,

, of the shaft so that it does not fail is ______ mm (rounded off to the nearest integer).

Diagram for Aerospace Engineering question 59

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A 10 kN axial load is applied eccentrically on a rod of square cross-section (1 cm

1 cm) as shown in the figure.

The strains measured by the two strain gages attached to the top and bottom surfaces at a distance of 0.5 m from the tip are

and

, respectively.

The eccentricity in loading,

, is ______ mm.

Diagram for Aerospace Engineering question 60

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GATE AE topic:aerospace-engineering PYQs

Question 51

Question 52

Question 53

Question 54

Question 55

Question 56

Question 57

Question 58

Question 59

Question 60