GATE AE topic:aerodynamics PYQs & Answers — Page 38

Questions 371–380 of 650. Imported answers require independent review unless marked reviewed.

Topic practice 650 questionsPage 38 of 65

A conventional fixed-wing aircraft, with a horizontal tail and vertical fin, in steady and level flight is subjected to small perturbations. Which of the following statement(s) is/are true?

Your answerSelect all correct options. You can choose more than one.

Vertical fin has a stabilizing effect on the lateral stability of the aircraft.

Vertical fin has a destabilizing effect on the directional stability of the aircraft.

Presence of wing anhedral increases the lateral stability of the aircraft.

Horizontal tail has a stabilizing effect on the longitudinal static stability of the aircraft.

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The ratio of the product of eigenvalues to the sum of the eigenvalues of the given matrix

is ______ (round off to nearest integer).

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The definite integral

is evaluated using four equal intervals by two methods – first by the trapezoidal rule and then by the Simpson’s one-third rule. The absolute value of the difference between the two calculations is ______ (round off to two decimal places).

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The deflection

of a certain beam of length

and uniform weight per unit length

, is given as

, where

is the distance from the point of support and

is a constant. The non-dimensional location

, where the deflection of the beam is maximum, is ______ (round off to two decimal places).

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A large water tank is fixed on a cart with wheels and a vane (see figure). The wheels of the cart provide negligible resistance for rolling on the fixed support. The cart is tied to the fixed support with a thin horizontal rope. There is a hole of diameter 5 cm on the side of the tank through which a jet of constant velocity of 10 m/s emerges. The jet of water is deflected by the attached vane by 60° (see figure). Assume that the jet velocity remains constant at 10 m/s after emerging from the vane. Take density of water to be 1000 kg/m

. The tension in the connecting rope is ______ N (round off to one decimal place).

Diagram for Aerospace Engineering question 40

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A finite wing of elliptic planform with aspect ratio 10, whose section is a symmetric airfoil, is placed in a uniform flow at 5 degrees angle of attack. The induced drag coefficient for the wing is ______ (round off to three decimal places).

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Consider a model of a boundary layer with the following velocity profile:

The shape factor, defined as the ratio of the displacement thickness to momentum thickness, for this profile is _____ (round off to 2 decimal places).

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An aircraft with a turbojet engine is flying at 270 m/s. The enthalpy of the incoming air at the intake is 260 kJ/kg and the enthalpy of the exhaust gases at the nozzle exit is 912 kJ/kg. The ratio of mass flow rates of fuel and air is equal to 0.019. The chemical energy (heating value) of fuel is 44.5 MJ/kg and the combustion process is ideal. The total loss of heat from the engine to the ambient is 25 kJ per kg of air. The velocity of the exhaust jet is __________ m/s (round off to two decimal places).

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Hot gases are generated at a temperature of 2100 K and a pressure of 14 MPa in a rocket chamber. The hot gases are expanded ideally to the ambient pressure of 0.1 MPa in a convergent-divergent nozzle having a throat area of 0.1 m². The molecular mass of the gas is 22 kg/kmol. The ratio of specific heats (γ) of the gas is 1.32. The value of the universal gas constant (R₀) is 8314 J/kmol-K. The acceleration due to gravity, g, is 9.8 m/s². The specific impulse of the rocket is ______ seconds (round off to two decimal places).

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A twin-spool turbofan engine is operated at sea level (Pₐ = 1 bar, Tₐ = 288 K). The engine has separate cold and hot nozzles. During static thrust test at sea level, the overall mass flow rate of air through the engine and the cold exhaust temperature are measured to be 100 kg/s and 288 K, respectively. The parameters for the engine are:

Fan pressure ratio = 1.6 Overall pressure ratio = 20 Bypass ratio = 3.0 Turbine entry temperature = 1800 K.

The specific heat at constant pressure (Cₚ) is 1.005 kJ/kg-K and the ratio of specific heats (γ) is 1.4 for air.

Assuming ideal fan and ideal expansion in the nozzle, the sea-level static thrust from the cold nozzle is ______________ kN (round off to two decimal places).

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GATE AE topic:aerodynamics PYQs

Question 36

Question 37

Question 38

Question 39

Question 40

Question 41

Question 42

Question 43

Question 44

Question 45