GATE AE purpose:exam-prep PYQs & Answers — Page 45

Questions 441–450 of 650. Imported answers require independent review unless marked reviewed.

Topic practice 650 questionsPage 45 of 65

A wing of 15 m span with elliptic lift distribution is generating a lift of 80 kN at a speed of 90 m/s. The density of surrounding air is 1.2 kg/m³. The induced angle of attack at this condition is ______ degrees (round off to two decimal places).

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A solid circular shaft, made of ductile material with yield stress

MPa, is subjected to a torque of 10 kNm. Using the Tresca failure theory, the smallest radius of the shaft to avoid failure is ______ cm (round off to two decimal places).

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The ratio of tangential velocities of a planet at the perihelion and the aphelion from the sun is 1.039. Assuming that the planet’s orbit around the sun is planar and elliptic, the value of eccentricity of the orbit is ______ (round off to three decimal places).

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The eigenvalues for phugoid mode of a general aviation airplane at a stable cruise flight condition at low angle of attack are

. If the acceleration due to gravity is 9.8 m/s², the equilibrium speed of the airplane is ______ m/s (round off to two decimal places).

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For a general aviation airplane with tail efficiency

, horizontal tail volume ratio

, downwash angle slope

, wing lift curve slope

rad⁻¹, horizontal tail lift curve slope

rad⁻¹, shift in neutral point location as a percentage of mean aerodynamic chord is ______ (round off to two decimal places).

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A single engine, propeller driven, general aviation airplane is flying in cruise at sea-level condition (density of air at sea-level is 1.225 kg/m³) with speed to cover maximum range. For drag coefficient

and wing loading

N/m², the speed of the airplane is ______ m/s (round off to one decimal place).

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The design flight Mach number of an ideal ramjet engine is 2.8. The stagnation temperature of air at the exit of the combustor is 2400 K. Assuming the specific heat ratio of 1.4 and gas constant of 287 J/(kg K), the velocity of air at the exit of the engine is ______ m/s (round off to one decimal place).

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The operating conditions of an aircraft engine combustor are as follows. The rate of total enthalpy of air entering the combustor = 28.94 MJ/s. The rate of total enthalpy of air leaving the combustor = 115.42 MJ/s. Mass flow rate of air = 32 kg/s. Air to fuel mass ratio = 15.6. Lower heating value of the fuel = 46 MJ/kg. The efficiency of the combustor is ______% (round off to two decimal places).

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The figure shows the T-S diagram for an axial turbine stage.

Diagram for Aerospace Engineering question 49

Assuming specific heat ratio of 1.33 for the hot gas, the isentropic efficiency of the turbine stage is _____% (round off to two decimal places).

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A rocket engine has a sea level specific impulse of 210 s and a nozzle throat area of 0.005 m². While testing at sea level conditions, the characteristic velocity and pressure for the thrust chamber are 190 m/s and 50 bar, respectively. Assume the acceleration due to gravity to be 9.8 m/s². The thrust produced by the rocket engine is ______ kN (round off to one decimal place).

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GATE AE purpose:exam-prep PYQs

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