GATE AE topic:aerodynamics PYQs & Answers — Page 13 — Exam Papers

Questions 121–130 of 650. Imported answers require independent review unless marked reviewed.

Topic practice 650 questionsPage 13 of 65

For a three-bar truss loaded as shown in the figure, the magnitude of the force in the horizontal member AB is ___ N (answer in integer).

Diagram for Aerospace Engineering question 56

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A uniform rigid bar of mass 3 kg is hinged at point F, and supported by a spring of stiffness k=100 N/m, as shown in the figure.

Diagram for Aerospace Engineering question 57

The natural frequency of free vibration of the system is ____ rad/s (answer in integer).

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A prismatic vertical column of cross-section

and length

is rigidly fixed at the bottom and free at the top. A compressive force P is applied along the centroidal axis at the top surface. The Young’s modulus of the material is 200 GPa and the uniaxial yield stress is 400 MPa. If the critical value of P for yielding and for buckling of the column are equal, the value of

is ____ (rounded off to one decimal place).

Diagram for Aerospace Engineering question 58

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A thin flat plate is subjected to the following stresses:

MPa;

MPa;

MPa.

Factor of safety is defined as the ratio of the yield stress to the applied stress. The yield stress of the material under uniaxial tensile load is 250 MPa. The factor of safety for the plate assuming that material failure is governed by the von Mises criterion is ____ (rounded off to two decimal places).

Diagram for Aerospace Engineering question 59

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Two designs A and B, shown in the figure, are proposed for a thin-walled closed section that is expected to carry only torque. Both A and B have a semi-circular nose and are made of the same material with a wall thickness of 1 mm. With strength as the only criterion for failure, the ratio of maximum torque that B can support to the maximum torque that A can support is__ (rounded off to two decimal places).

Diagram for Aerospace Engineering question 60

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An ideal turbofan with a bypass ratio of 5 has core mass flow rate,

kg/s. The core and the fan exhausts are separate and optimally expanded. The core exhaust speed is 600 m/s and the fan exhaust speed is 120 m/s. If the fuel mass flow rate is negligible in comparison to

, the static specific thrust (

) developed by the engine is ____ N s/kg (rounded off to the nearest integer).

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Air at temperature 300 K is compressed isentropically from a pressure of 1 bar to 10 bar in a compressor. Eighty percent of the compressed air is supplied to a combustor. In the combustor, 0.8 MJ of heat is added per kg of air. The specific heat at constant pressure is

J/kg/K and the specific heat ratio is

. The temperature of the air leaving the combustor is ____ K (rounded off to one decimal place).

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A monopropellant liquid rocket engine has 800 injectors of diameter 4 mm each, and with a discharge coefficient of 0.65. The liquid propellant of density 100 kg/m

flows through the injectors. There is a pressure difference of 10 bar across the injectors. The specific impulse of the rocket is 1500 m/s. The thrust generated by the rocket is ____ kN (rounded off to one decimal place).

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An ideal ramjet with an optimally expanded exhaust is travelling at Mach 3. The ambient temperature and pressure are 260 K and 60 kPa, respectively. The inlet air mass flow rate is 50 kg/s. Exit temperature of the exhaust gases is 700 K. Fuel mass flow rate is negligible compared to air mass flow rate. Gas constant is R= 287 J/kg/K, and specific heat ratio is

. The thrust generated by the engine is ____ kN (rounded off to one decimal place).

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A single-stage axial compressor, with a 50 % degree of reaction, runs at a mean blade speed of 250 m/s. The overall pressure ratio developed is 1.3. Inlet pressure and temperature are 1 bar and 300 K, respectively. Axial velocity is 200 m/s. Specific heat at constant pressure,

J/kg/K and specific heat ratio,

. The rotor blade angle at the outlet is ____ degrees (rounded off to two decimal places).

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