GATE AE year:2018 PYQs & Answers — Page 6

Questions 51–60 of 65. Imported answers require independent review unless marked reviewed.

Topic practice 65 questionsPage 6 of 7

A statically-stable aircraft has a

(where the angle of attack,

, is measured in radians). The coefficient of moment of the aircraft about the center of gravity is given as

. The mean aerodynamic chord of the aircraft is 1 m. The location (positive towards the nose) of the neutral point of the aircraft from the center of gravity is _____ (in m, accurate to two decimal places).

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An aircraft with a gross weight of 2000 kg, has a speed of 130 m/s at sea level, where the conditions are: 1 atmosphere (pressure), 288 K (temperature), and 1.23 kg/m

(density). The speed (in m/s) required by the aircraft at an altitude of 9000 m, where the conditions are: 0.31 atmosphere, 230 K, and 0.47 kg/m

, to maintain a steady, level flight is ______ (accurate to two decimal places).

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A pitot probe on an aircraft in a steady, level flight records a pressure of 55,000 N/m

. The static pressure and density are 45,280 N/m

and 0.6 kg/m

, respectively. The wing area and the lift coefficient are 16 m

and 2, respectively. The wing load (in N/m

) on this aircraft is ________ (accurate to one decimal place).

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A spacecraft forms a circular orbit at an altitude of 150 km above the surface of a spherical Earth. Assuming the gravitational parameter,

and radius of earth, Re = 6,400 km, the velocity required for the injection of the spacecraft, parallel to the local horizon, is ______________ (accurate to two decimal places).

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Air at 50 kPa pressure and 400 K temperature flows in a duct at Mach 3.0. A part of the flow leaks through an opening on the duct wall into the ambient, where the pressure is 30 kPa. The maximum Mach number achieved in the discharge is ______ (accurate to two decimal places). (Ratio of specific heats of air is

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Consider a 20° half-angle wedge in a supersonic flow at Mach 3.0 at standard sea-level conditions. If the shock-wave angle on the wedge is 36°, the Mach number of the tangential component of the flow post-shock is ______ (accurate to two decimal places).

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The boundary layer thickness at the location of a sensor on a flat plate in an incompressible, laminar flow of air is required to be restricted to 1 mm for an effective measurement. If the flow velocity is 20 m/s with 1 bar pressure, 300 K temperature, and 1.789×10

kg/(m-s) viscosity, the maximum distance (in mm) of the sensor location from the leading edge is _______ (accurate to one decimal place).

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Gross weight of an airplane is 700 N, wing area is 16 m

, and the maximum lift coefficient is 2.0. Assuming density at the altitude as 1.23 kg/m

, the stall speed (in m/s) of the aircraft is _______ (accurate to two decimal places).

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A thin-walled tube with external radius of 100 mm and wall thickness of 2 mm is fixed at one end. It is subjected to a compressive force of 1 N acting at a point on the circumference parallel to its length. The maximum normal stress (in kPa) experienced by the structure is __________ (accurate to two decimal places).

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A 1 m long massless cantilever beam oscillates at 2 Hz, while a 60 kg mass is attached at the tip of it. The flexural rigidity of the beam (in kN-m

) is __________________ (accurate to two decimal places).

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GATE AE year:2018 PYQs

Question 41

Question 42

Question 43

Question 44

Question 45

Question 46

Question 47

Question 48

Question 49

Question 50