GATE AE discipline:aerospace-engineering PYQs & Answers — Page 39

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Questions 381–390 of 650. Imported answers require independent review unless marked reviewed.

Topic practice 650 questionsPage 39 of 65

At the design conditions, the velocity triangle at the mean radius of a single stage axial compressor is such that the blade angle at the rotor exit is equal to 30°. The absolute velocities at the rotor inlet and exit are equal to 140 m/s and 240 m/s, respectively. The flow velocities relative to the rotor at inlet and exit of the rotor are equal to 240 m/s and 140 m/s, respectively.

Diagram for Aerospace Engineering question 46

The blade speed (

) at the mean radius of the rotor is __________ m/s (round off to two decimal places).

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A single stage axial turbine has a mean blade speed of 340 m/s at design condition with blade angles at inlet and exit of the rotor being 21° and 55°, respectively. The degree of reaction at the mean radius of the rotor is equal to 0.4. The annulus area at the rotor inlet is 0.08 m² and the density of gas at the rotor inlet is 0.9 kg/m³. The flow rate through the turbine at these conditions is _________ kg/s (round off to two decimal places).

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The air flow rate through the gas generator of a turboprop engine is 100 kg/s. The stagnation temperatures at inlet and exit of the combustor are 600 K and 1200 K, respectively. The burner efficiency is 90% and the heating value of the fuel is 40 MJ/kg. The specific heats at constant pressure (Cₚ) for air and burned gases are 1000 J/kg-K and 1200 J/kg-K, respectively. The flow rate of the fuel being used is ______________ kg/s (round off to two decimal places).

(Note: Do not neglect the fuel flow rate with respect to the air flow rate)

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A rigid horizontal bar ABC, with roller support at A, is pinned to the columns BD and CE at points B and C, respectively as shown in figure. The other end of the column BD is fixed at D, whereas the column CE is pinned at E. A vertical load P is applied on the bar at a distance ‘a’ from point B. The two columns are made of steel with elastic modulus 200 GPa and have a cross section of 1.5 cm x 1.5 cm. The value of ‘a’ for which both columns buckle simultaneously, is __________ cm (round off to one decimal place).

Diagram for Aerospace Engineering question 49

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A two-cell wing box is shown in the figure. The cell walls are 1.5 mm thick and the shear modulus

GPa. If the structure is subjected to a torque of 12 kNm, then the wall AD will experience a shear stress of magnitude __________ MPa (round off to one decimal place).

Diagram for Aerospace Engineering question 50

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Two cantilever beams AB and DC are in contact with each other at their free ends through a roller as shown in the figure. Both beams have a square cross section of 50 mm x 50 mm, and the elastic modulus E = 70 GPa. If beam AB is subjected to a uniformly distributed load of 20 kN/m, then the compressive force experienced by the roller is __________ kN (round off to one decimal place).

Diagram for Aerospace Engineering question 51

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A 3 m x 1 m signboard is supported by a vertical hollow pole that is fixed to the ground. The pole has a square cross section with outer dimension 250 mm. The yield strength of the pole material is 240 MPa. To sustain a wind pressure of 7.5 kPa, the dimension d of the pole is __________ mm (round off to nearest integer).

(Neglect the effect of transverse shear and load due to wind pressure acting on the pole)

Diagram for Aerospace Engineering question 52

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An airplane weighing 5500 kg is in a steady level flight with a speed of 225 m/s. The pilot initiates a steady pull-up maneuver with a radius of curvature of 775 m. The location of center of gravity (CG), center of pressure on wing (CP) and point of action (T) of tail force are marked in the figure. Use g = 9.81 m/s². Neglect drag on the tail and assume that tail force is vertical. Assuming the engine thrust and drag to be equal, opposite and collinear, the tail force is______________ kN (round off to one decimal place).

Diagram for Aerospace Engineering question 53

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A jet aircraft weighing 10,000 kg has an elliptic wing with a span of 10 m and area 30 m

. The

for the aircraft is 0.025. The maximum speed of the aircraft in steady and level flight at sea level is 100 m/s. The density of air at sea level is 1.225 kg/m

, and take

m/s

. The maximum thrust developed by the engine at sea level is _____ N (round off to two decimal places).

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Consider a jet transport airplane with the following specifications:

Lift curve slope for wing-body

/deg Lift curve slope for tail

/deg Tail area

Wing area

Distance between mean aerodynamic centers of tail and wing-body

m Mean aerodynamic chord

m Downwash

Axial location of the wing-body mean aerodynamic center

Axial location of the center of gravity

All axial locations are with respect to the leading edge of the root chord and along the body x-axis. Ignore propulsive effects.

The pitching-moment-coefficient curve slope (

) is ______ /deg (round off to three decimal places).

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GATE AE discipline:aerospace-engineering PYQs

Question 46

Question 47

Question 48

Question 49

Question 50

Question 51

Question 52

Question 53

Question 54

Question 55