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Aerospace Engineering Gate 2013 Questions with Answer
Ques 40 GATE 2013
Given that the Laplace transform, L(eat)=1/(s-a) then L(3e5tsinh 5t)=
Ques 41 GATE 2013
Values of a, b and c, which render the matrix
Ques 42 GATE 2013
A function y(t) satisfies the differential equation d2y/dt2-2dy/dt+y=0 and is subject to the initial conditions y(t=0)=0 and dy/dt(t=0)=1. The value of y(t=1) is
Ques 43 GATE 2013
The Headmaster _______ to speak to you. Which of the following options is incorrect to complete the above sentence?
Ques 44 GATE 2013
Mahatama Gandhi was known for his humility as
Ques 45 GATE 2013
Which of the above underlined parts of the sentence is not appropriate?
Ques 46 GATE 2013
Which one of the following is the most stable configuration of an airplane in roll?
Ques 47 GATE 2013
A supersonic airplane is expected to fly at both subsonic and supersonic speeds during its whole flight course. Which one of the following statements is TRUE?
Ques 48 GATE 2013
Which one of the following is TRUE with respect to Phugoid mode of an aircraft?
Ques 49 GATE 2013
A damped single degree-of-freedom system is vibrating under a harmonic excitation with an amplitude ratio of 2.5 at resonance. The damping ratio of the system is
Ques 50 GATE 2013
Consider an airplane with rectangular straight wing at dihedral angle Γ=100 Lift curve slope of wing airfoil section (constant over the whole span of the wing) is clα=5.4/rad The roll stability derivative, Clβ in per radian is
Ques 51 GATE 2013
A wing-body alone configuration airplane with a wing loading of W/S = 1000 N/m2 is flying in cruise condition at a speed V = 90 m/s at sea-level (air density at sea-level ρ∞ = 1.22 kg/m3).
The zero lift pitching moment coefficient of the airplane is Cmacwb = Cm0 = –0.06
and the location of airplane aerodynamic center from the wing leading edge is Xac = 0.25c.
Here c is the chord length.
The airplane trim lift coefficient CL~win is
Ques 52 GATE 2013
A wing-body alone configuration airplane with a wing loading of W/S = 1000 N/m2 is flying in cruise condition at a speed V = 90 m/s at sea-level (air density at sea-level ρ∞ = 1.22 kg/m3).
The zero lift pitching moment coefficient of the airplane is Cmacwb = Cm0 = –0.06
and the location of airplane aerodynamic center from the wing leading edge is Xac = 0.25c.
Here c is the chord length.
Distance of center of gravity of the aircraft (XCG) from the wing leading edge is
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