GATE AE topic:aerospace-engineering PYQs & Answers — Page 64

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Questions 631–640 of 650. Imported answers require independent review unless marked reviewed.

Topic practice 650 questionsPage 64 of 65

The given diagram represents the velocity triangles at the leading edge (1) and trailing edge (2) at the mean radius of a single stage axial compressor rotor. The stage efficiency of the compressor is 0.8. The stagnation temperature of air entering the stage is 298 K and the specific heat at constant pressure for air is 1.005 kJ/kgK. The ratio of specific heats for air is 1.4. Considering actual work in the rotor is equal to the ideal work, the pressure ratio for the stage is equal to ________ (in two decimal points).

Diagram for Aerospace Engineering question 46

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An aircraft with a turbojet engine, having an inlet area of 1 m², is flying at 270 m/s at an altitude where the atmospheric pressure is equal to 0.9 bar and the ambient temperature is equal to 290 K. The stagnation pressure and temperature at the exit of the turbine are equal to 1.6 bar and 774 K respectively. The specific heat at constant pressure of the burned gases is equal to 1.147 kJ/kgK and the ratio of specific heats is equal to 1.33. Considering ideal expansion in the nozzle with no losses, the specific thrust produced by the engine is ________ Ns/kg (in one decimal place).

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Air, at 450 K station temperature and at a rate of 50 kg/s, enters the combustor of a turbofan engine and is burned with 1 kg/s of Aviation Kerosene (Heating value 44 MJ/kg). The specific heat at constant pressure for the incoming air and the burned products are 1.005 kJ/kgK and 1.147 kJ/kgK respectively. Considering 100% burner efficiency, the station temperature at the exit of the combustor is equal to ________ K. (in one decimal place).

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A single stage chemical rocket, having an initial mass of 10,000 kg and specific impulse of 450 s, is launched from the surface of the earth and has to reach the escape velocity (11 km/s) at burn out. Consider

m/s². If the atmospheric drag and the effect of gravity are to be neglected, the mass of propellant to be carried by the rocket is equal to ________ kg (in one decimal place).

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A centrifugal compressor requires 1800 kW of power to compress 10 kg/s of air. Consider the whirl velocity component is equal to the impeller speed (i.e., no slip) and no losses in the impeller. If the impeller has to rotate at 1900 rad/s, the diameter of the impeller is to be ________ m (in two decimal place).

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An aircraft wing is idealized as a cantilever beam of constant width and length

with a tip mass of weight

(Newtons) and has a uniformly distributed loading of

(Newtons/m) as shown in the figure. Flexural rigidity = EI and

. The upward deflection of the tip of the aircraft wing under the given loading can be expressed as:

. The value of

is ________ (in three decimal places).

Diagram for Aerospace Engineering question 51

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For the state of plane stress shown in the figure, the minimum principal stress is

. The normal stress

is equal to ________ (round to nearest integer).

Diagram for Aerospace Engineering question 52

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The maximum normal stress in MN/m² for the thin walled beam of square cross section of outer dimension 120 mm x 120 mm and wall thickness 1 mm under the action of moment

Nm as shown in the figure is ________ (in three decimal places).

Diagram for Aerospace Engineering question 53

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The idealized cross section of a thin-walled wing box structure shown in the figure is subjected to an anticlockwise torque of 10 kNm. The corresponding shear-flow distribution under this loading condition is shown in the figure. The area of each cell is

mm² and

mm². The ratio of the unknown

is given by ________ (in three decimal places).

Diagram for Aerospace Engineering question 54

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The natural frequency of the system suspended by two identical springs of stiffness

as shown in the figure is given by

for small displacement. Both the springs make an angle of 45° with the horizontal. The value of

is ________ (in two decimal places).

Diagram for Aerospace Engineering question 55

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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