GATE AE topic:aerospace-engineering PYQs & Answers — Page 12

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Questions 111–120 of 650. Imported answers require independent review unless marked reviewed.

Topic practice 650 questionsPage 12 of 65

An aircraft is flying at an altitude of 4500 m above sea level, where the ambient pressure, temperature and density are 57 kPa, 259 K and 0.77 kg/m

, respectively. The speed of the aircraft (

) is 230 m/s. Gas constant

J/kg/K, and specific heat ratio

. If the stagnation pressure is

, and static pressure is

, the value of

(rounded off to two decimal places).

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A rectangular wing of 1.2 m chord length and aspect ratio 5 is tested in a wind tunnel at an air speed of 60 m/s. The density and the dynamic viscosity of air are 1.3 kg/m

and

kg/m-s, respectively. A second rectangular wing of the same span, but with an aspect ratio of 6, is to be tested in the same tunnel at the same Reynolds number. The air speed at which the second test should be performed is

m/s (answer in integer).

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In a low-speed airplane, a venturimeter with 1.3:1 area ratio is used for airspeed measurement. The airplane’s maximum speed at sea level is 90 m/s. If the density of air at sea level is 1.225 kg/m

, the maximum pressure difference between the inlet and the throat of the venturimeter is

kPa (rounded off to two decimal places).

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A supersonic stream of an ideal gas at Mach number

is turned by a ramp, as shown in the figure. The ramp angle is 20°. The pressure ratio is

and the specific heat ratio is

. The pressure coefficient on the ramp surface is

(rounded off to two decimal places).

Diagram for Aerospace Engineering question 49

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A perfect gas flows through a frictionless constant-area duct with heat addition. The inlet conditions are as follows: pressure 100 kPa, density 1 kg/m

, and velocity 100 m/s. At a particular downstream location, the gas velocity is 200 m/s. The static pressure at the downstream location is

kPa (answer in integer).

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The mass flow rate in a supersonic wind tunnel is 2 kg/s when the stagnation pressure and stagnation temperature are 1 MPa and 800 K, respectively. If the stagnation pressure and stagnation temperature are changed to 3 MPa and 200 K, the mass flow rate in the tunnel changes to

kg/s (answer in integer).

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A jet-powered airplane is steadily climbing at a rate of 10 m/s. The air density is 0.8 kg/m

, and the thrust force is aligned with the flight path. Using the information provided in the table below, the airplane’s thrust to weight ratio is

(rounded off to one decimal place).|Airplane speed|80 m/s| |---|---| |Lift coefficient,

|0.8| |Aspect ratio|6| |Oswald efficiency factor|0.8| |Zero-lift drag coefficient|0.02|

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F and G denote two points on a spacecraft’s orbit around a planet, as indicated in the figure. O is the center of the planet, P is the periapsis, and the angles are as indicated in the figure. If OF = 8000 km, OG = 10000 km,

deg, and

deg, the eccentricity of the spacecraft’s orbit is

(rounded off to two decimal places).

Diagram for Aerospace Engineering question 53

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While taking off, the net external force acting on an airplane during the ground roll segment can be assumed to be constant. The airplane starts from rest.

and

are the ground roll distance and the lift-off speed, respectively.

(

) denotes the airplane speed at

. Neglecting changes in the airplane mass during the ground roll segment, the value of

(rounded off to two decimal places).

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A 1 m long rod of 1 cm × 1 cm cross section is subjected to an axial tensile force of 35 kN. The Young’s modulus of the material is 70 GPa. The cross-section of the deformed rod is 0.998 cm × 0.998 cm. The Poisson’s ratio of the material is

(rounded off to one decimal place).

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GATE AE topic:aerospace-engineering PYQs

Question 46

Question 47

Question 48

Question 49

Question 50

Question 51

Question 52

Question 53

Question 54

Question 55