GATE exam solved papers of previous year solved papers ?

Hi buddy can you plz provide me solved papers of GATE of last year?????

[Arun Vats]

Here you are looking for GATE exam but you didn’t mention subject for which you are looking here, so I would like to tell you that I have its paper of all following paper:

AE: Aerospace Engineering
AG: Agricultural Engineering
AR: Architecture and Planning
BT: Biotechnology
CE: Civil Engineering
CH: Chemical Engineering
CS: Computer Sc. and Information Technology
CY: Chemistry
EC: Electronics and Communication Engg.
EE: Electrical Engineering
GG: Geology and Geophysics
IN: Instrumentation Engineering
MA: Mathematics
ME: Mechanical Engineering
MN: Mining Engineering
MT: Metallurgical Engineering
PH: Physics
PI: Production and Industrial Engineering
TF: Textile Engineering and Fibre Science
XE: Engineering Sciences
XL: Life Sciences

For your reference I am providing GATE Aerospace Engineering paper if you are looking for any other paper then let me know so I can provide you same:

GATE Aerospace Engineering paper

Q. 1 – Q. 25 carry one mark each.
Q.1 The constraint A2 = A on any square matrix A is satisfied for
(A) the identity matrix only. (B) the null matrix only.
(C) both the identity matrix and the null matrix. (D) no square matrix A.
Q.2
The general solution of the differential equation
2
2 2 0 d y dy y
dt dt
+ − = is
(A) 2 t t Ae Be − + (B) 2t t Ae Be − − + (C) 2t t Ae Be − + (D) 2 t t Ae Be +
Q.3 An aircraft in trimmed condition has zero pitching moment at
(A) its aerodynamic centre. (B) its centre of gravity.
(C) 25% of its mean aerodynamic chord. (D) 50% of its wing root chord.
Q.4 In an aircraft, constant roll rate can be produced using ailerons by applying
(A) a step input. (B) a ramp input.
(C) a sinusoidal input. (D) an impulse input.
Q.5 For a symmetric airfoil, the lift coefficient for zero degree angle of attack is
(A) – 1.0 (B) 0.0 (C) 0.5 (D) 1.0
Q.6 The critical Mach number of an airfoil is attained when
(A) the freestream Mach number is sonic.
(B) the freestream Mach number is supersonic.
(C) the Mach number somewhere on the airfoil is unity.
(D) the Mach number everywhere on the airfoil is supersonic.
Q.7 The shadowgraph flow visualization technique depends on
(A) the variation of the value of density in the flow.
(B) the first derivative of density with respect to spatial coordinate.
(C) the second derivative of density with respect to spatial coordinate.
(D) the third derivative of density with respect to spatial coordinate.
Q.8 The Hohmann ellipse used as earth-Mars transfer orbit has
(A) apogee at earth and perigee at Mars. (B) both apogee and perigee at earth.
(C) apogee at Mars and perigee at earth. (D) both apogee and perigee at Mars.
Q.9 The governing equation for the static transverse deflection of a beam under an uniformly distributed
load, according to Euler-Bernoulli (engineering) beam theory, is a
(A) 2nd order linear homogenous partial differential equation.
(B) 4th order linear non-homogenous ordinary differential equation.
(C) 2nd order linear non-homogenous ordinary differential equation.
(D) 4th order nonlinear homogenous ordinary differential equation.
Q.10 The Poisson’s ratio, νof most aircraft grade metallic alloys has values in the range:
(A) −1 ν ≤ ≤0 (B) 0 ν ≤ ≤0.2 (C) 0.2 ν ≤ ≤ 0.4 (D) 0.4 ν ≤ ≤0.5









For see complete paper here is attachment: