© GATE AEROSPACE FORUM
Free or Demo test for GATE-2010 All India Test Series In Aerospace(sectional test)
AE: Aerospace Engineering
Duration: 3 hours
MM: 100
Read the Following Instructions Carefully
1. This question paper contains 60 objective type questions. Q.1 to Q.20
carry one mark each and Q.21 to Q.60 carry two marks each.
2. Attempt all the questions.
3. Question must be answered on objective response sheet by darkening
the appropriate bubble (mark the abcd) using HB pencil against the
Question number on the left hand side of the OMR. Each Question has
only one correct answer. In case if you wish to change the answer
erase the old answer completely. And send the OMR to email ID.
4. Wrong answer will carry NEGATIVE MARKS. In Q.1 to Q.20, 1/3 marks
will be deducted for each answer. In Q.21 to Q.56, Q57, Q.59, 2/3 mark
will be deducted for each wrong answer. How ever there will be no
negative marking in Q.58 & Q.60. More then one answer bubbled
against a question will be taken as incorrect response. Unattempted
question will not carry any marks.
5. Using the HB pencil darken the appropriate bubble under each digit of
your registration number and the letters corresponding to your paper
code.
6. Calculator usage is allowed.
7. Charts, graphs sheets or tables are not allowed.
8. Rough work can be done on the question paper it self. Additionally
blank pages are given at the end of the question paper for rough work.
9. This question paper contains 15 printed pages . Please check all pages .
For more information log on to www.gateaerospaceforum.com
Page 1
© GATE AEROSPACE FORUM
Q.1) L [ e3t cos 4 ] equals to
b) ()
a)() ()
c) ()
d) ()
Q.2) L[tnf(t)] equals to
a) [ ()]
c) (-1)n
b)(-1)n [ ()]
[ ()]
d) (-1)
[ ()]
Q.3) The general solution of the equation = is
a) +Cey+1=0
b) +Cex+1=0
c) +ex+2=0
d) +ey-1=0
Q.4) The order of the differential equation of the family of curves ax2+by2=c is
a)2
b)3
c)1
d)None of these
Q.5) The shear stress in a circular shaft under torsion varies
a) Uniformly
d) linearly
c) parabolically
d) hyperbolically
Q.6) Shear strain energy per unit volume may be written as
a) [( − ) + ( − ) + ( − ) ]
b)
[( − ) + ( − ) + ( − ) ]
c) [( − ) + ( − ) + ( − ) ]
For more information log on to www.gateaerospaceforum.com
Page 2
© GATE AEROSPACE FORUM
d)
[( − ) + ( − ) + ( − ) ]
Q7.) A column of solid circular cross-section and length L can have various end condition. Choose the
correct set that matches the end condition (listed in group I) with the corresponding effective length for
buckling (listed in group II).
Group I (end conditions)
(P)One end built in and other end free
(Q)both ends pinned
(R) both ends built in
(S) one end built-in and other end pinned
a) P-3
b)P-4
c)P-2
Group II(effective length )
(1)1.0L
(2)0.7L
(3)2.0 L
(4)0.5L
d)P-3
Q-1
Q-1
Q-1
Q-1
R-4
R-2
R-3
R-2
S-2
S-3
S-4
S-4
Q.8) For two shafts connected in parallel find which statement is true
a) Torque in each shaft is the same
b) Shear stress in each shaft is the same
c) Angle of twist of each shaft is the same
d) Torsional stiffness of each shaft is the same
Q.9)The maximum thickness to chord ratio for the NACA 24014 airfoil is
a) 0.01
b) 0.14
c) 0.24
d) 0.40
Q.10) Laminar flow airfoils are used to reduce
a) Trim drag
b) skin friction drag
c) Induced drag
d) wave drag
Q.11) According to kutta-joukowski theorem, the circulation at the trailing edge of the airfoil is
For more information log on to www.gateaerospaceforum.com
Page 3
© GATE AEROSPACE FORUM
A) 0
b) finite
c) infinite
d) one unit
Ques.12 Consider the lifting flow ones a circular cylinder with given radius and circulation. If !∞ is
doubled keeping the circulation same then the shape of the streamline
(a). will remain same
(b). will change in upper half
(c). will change in lower half
(d). will change in both portion
Q.13) According to thin airfoil theory of symmetric airfoil the quarter code point is
a) Centre of pressure point
b) aerodynamic centre point
c) Both a & b.
c) None of these
Q.14) For an elliptic orbit of satellite, let the smallest distance form centre of primary be "#$% and
(
greatest distance "#& . Then ' ) *(sectorial velocity) for the satellite in terms of "#$% +,- "#& is
Where you assume primary is earth and K=√/0, = 22,"3234 56 773832 5"93
a=
:;< :;=>
C
a)
?@ (A)&B
c)
?@ (A)&B
C
b)
?@ ?A B&B
d)
?@ ?A B&B
C
C
D
D
Q.15) For a fixed centre of gravity location of an airplane, when the propeller is mounted on the nose of
the fuselage
a) Longitudinal static stability increases.
b) Longitudinal static stability decreases
c) Longitudinal static stability remains same.
For more information log on to www.gateaerospaceforum.com
Page 4
© GATE AEROSPACE FORUM
d) Longitudinal static stability is maximum.
Q.16) let an airplane in a steady level flight be trimmed at a certain speed. A level and steady flight at a
higher speed could be achieved by changing
A) Engine throttle only.
b) Elevator only.
c) Throttle and elevator together.
d) Rudder only.
Q.17) An airplane model with a symmetric airfoil was tested in a wind tunnel .Cmo (Cm at angle of attack,
α=0) was estimated to be 0.08 and 0 respectively for elevator settings (E ) of 5 degree up and 5 degrees
FG
down. The estimated value of the elevator control power ( FHA; ) of the model will be
a) 0.07 per degree
b)-1.065 per degree
b)-0.008 per degree
c)-0.762 per degree
Q.18) A centrifugal pump is discharging 4500lit/min and operates at 1800rpm.If this pump is required to
operate at 1200rpm assuming its efficient remains same then the discharge is
a) 3000 lit/min
b)4000 lit/min
c)4500 lit/min
d)1500 lit/min
Q.19) By shock-free entry is meant
a) That the flow should enter the runner smoothly
b) That the relative velocity vector should have the same direction as that of the tangent at the inlet tip
of the blade.
c) That the absolute velocity vector should be tangential at the inlet tip of the blade.
d) That the velocity of the flow should be natural.
Q.20)which one of the following values is nearer to the vacuum specific impulse of a rocket engine using
liquid hydrogen and liquid oxygen as propellants.
a)49 sec
b)450 sec
c)6000sec
d)40000sec
For more information log on to www.gateaerospaceforum.com
Page 5
© GATE AEROSPACE FORUM
FOR TWO MARKS EACH
Q.21) The order of the differential equation of the family of all circles in the xy-plane with their centers
lying on the parabola x=y2 is
a) 1
b) 2
c) 3
I d) 4
Q.22) The differential equation I + 3 + − 4=0 with the boundary conditions y (1) =5 and y (2) =7
has
a) No solution
b) a unique solution
c) Three solutions
d) None of the above
N KLM )KLM D)
Q.23) JO
)
-, equals to
a) Log2/3
b) log3/2
c) log1/3
d) log1/2
b)e-tsin3t
c) etsin2t
d) e-tsin2t
Q.24) L-1 (()P)=
a)etsin3t
Q.25) solve Q + Q – 4y=Q a) y=C1x2 + C2 −
c)y = C1 x2 +C2 +
FU
RST
b) y = C1 +C2 x2 −
D
RST
d) y=C1 Q +C2 x +
D
RST
D
RST
D
FU
Q.26) If p=F & q=F , then the partial differential equation from Q + 4 + (V − 2) = W ,where a & c
are arbitrary constants is
a)X = Y
b) Y = X
c) X = Y
For more information log on to www.gateaerospaceforum.com
d) Y = X
Page 6
© GATE AEROSPACE FORUM
Q.27) x − 4 = QZQ + 4 , then the solution is, where A is a constant
b) [1 + + = ] d) [1 + + = ] a)[1 + − = ] c) [1 − + = ] Q.28) The von Mises yield criterion or the maximum distortion energy criterion for a plane stress
problem with and as the principal stresses in the plane and as the yield stress requires
a) − + ≤ b)| | ≤ c)| | ≤ d) | | ≤ Q.29) An Euler-Bernoulli beam having a rectangular cross-section as shown in the figure, is subjected to
non-uniform bending moment along its length.!U =
cross-section is given by
b
. The shear stress distribution aU across its
U
fg
e
b) aU =
U
d) aU =
a) aU = dc
b
`
c) aU = c (f )
d
e
g
z
bc?fgB
bc?fgB
de
(1 −
U
(fg)
)
de
!U
y
h
b
Q.30)A beam of I cross-section, as shown in fig. is subjected to a shear force V=100KN. The stress on the
section AA (with 5.6304 x 106 mm4)(A=1920 mm2) is
For more information log on to www.gateaerospaceforum.com
Page 7
© GATE AEROSPACE FORUM
a)|aU |=11.19 MPa
b) |a |=11.19 MPa
c) |aU |=52.08 MPa
d) |a |=52.08 MPa
Q.31) A circular rod of length L and torsional rigidity GJ is fixed at one end and free at the other end if a
twisting moment T is applied at a distance of L/2 from the fixed end, the angle of twist at free end will
be
hi
hi
a)j
b) j
c)
hi
d)
j
hi
j
Q.32) The bending moment distribution in a beam as a function of distance x is given by M=5x2+20x-7Nm the shear force at x=2m is
a) 0
b) 10N
c) 20N
For more information log on to www.gateaerospaceforum.com
d) 40N
Page 8
© GATE AEROSPACE FORUM
Q.33) A beam of rectangular cross –section is subjected to transverse loads.In a section where the shear
stress at 1/4th of the beam depth is 120 MPa,the maximum shear stress is
a)130 MPa
b)160 MPa
c)200 MPa
d)240 MPa
Q.34) A thin wire of 2mm diameter with young’s modulus 200GPa is wrapped around a drum of
diameter 8m. The maximum bending stress in the wire is
a)20MPa
b)25MPa
c)40MPa
d)50MPa
Q.35) If a thin spherical shell is subjected to an internal pressure then change in volume will be equal to
kX
b)
kX
d)
kX
a) D)l '1 − #*
c)
kXn
m)l
(1 − #)
m)l
m)l
'1 − *
#
(1 − #)
Q.36) the hydraulic efficiency of a turbine is defined as
a) The ratio of power utilized by runner to that supplied by the water at entry to the turbine.
b) The ratio of power supplied by water at entry to the power utilized by runner.
c) The ratio of power available at the turbine shaft to that supplied to it by the runner
d) The ratio of power supplied by the runner to the power available at the shaft
Q.37) The following table list various kinds of boundary layer thickness and the corresponding equation
are given in the second column, not necessarily in that order. Match each boundary-layer thickness with
its mathematical-equivalent expression
Column -1
column-2
A) Nominal thickness
1)JO
B) Displacement thickness
2) y=Efor u=0.09rN
C) Momentum thickness
3) JO
H o
For more information log on to www.gateaerospaceforum.com
pq
H o
'1 −
pq
o
pq
'1 −
* -4
o
pq
* -4
Page 9
© GATE AEROSPACE FORUM
H
o
4) JO '1 − p * -4
D) Energy thickness
A)
B)
c)
d)
a)
2
4
1
3
b)
1
2
2
2
c)
3
1
3
4
d)
4
3
4
1
q
Q.38) Experiment were conducted in a wind tunnel with a wind speed of 60 Km/hr on a flat plate 2m
long and 1m wide. The specific weight of air is 1.15kg/m3. The plate is kept at such an angle that the
coefficients of lift and drag are 0.75 and 0.15 respectively. What are the lift and drag forces?
a) 239.7 N, 57.9N
b) 293.7N, 57.9 N
c) 239.7 N,47.9N
d) 293.7 N.47.9 N
Q.39) Suppose the gravitational force varies inversely as the nth power of the distance. Then the time
period of a planet in circular orbit of radius R around the sun will be proportional to
a) R-n
b) Rn
c) R(n-1)/2
d) R(n+1)/2
Q.40)The largest and shortest distance of earth from the sun are r1 and r2 .Its distance from the sun
when it is perpendicular to the major axis of the orbit drawn form the sun is
a)
:C :
D
: :
:C :
b) :C :
C
c) :
d)
C :
:C :
Q.41)A missile is launched with a velocity less then zero escape velocity. The sum of its kinetic energy
and potential energy is
a) Positive
b) Negative
c) Zero
d) May be positive or negative depending upon its initial velocity.
For more information log on to www.gateaerospaceforum.com
Page 10
© GATE AEROSPACE FORUM
Q.42)A satellite is moving around the earth with the speed v in a circular orbit of radius r,if the orbit
radius is decreased by 1% its speed will
a)increase by 1%
b)increase by 0.5 %
c)decrease by 1%
d)decrease by 0.5 %
Q.43) what is the velocity change required to transfer a satellite from a circular 600Km orbit with an
indination of 28 degree to an orbit of equal size with an inclination of 20degree.(Re=6378Km)
a) 1054 m/s
b)1554 m/s
c)554m/s
d)2054m/s
Q.44) An airfoil section is known to generate lift when placed in a uniform stream of speed rN at an
incidence ∝ .A biplane consisting of two such section of identical Chord C, separated by a distance h is
shown in the following figure:
With regards to this biplane which of the following statement is true?
a) Both the airfoil experiences an up wash and an increased approach velocity.
b) Both the airfoil experiences an down wash and a decreased approach velocity.
c) Both the airfoil experiences an up wash and airfoil A experiences a decreased approach velocity while
airfoil B experiences a increased approaches velocity.
d) The incidence for the individual sections of the biplane is not altered
Q.45) An ideal ramjet is flying at a Mach number M. The exhaust gas static temperature at the outlet of
the nozzle is Te. The ambient static temperature is Ta. Gas constant R and specific heat ratio t do not
very through the ramjet. Assuming that nozzle exhaust static pressure is equal to the ambient pressure
and fuel air ratio f<<<1, the thrust per unit mass flow rate is
h
h
a)Ztuv& w[hx y
b) Ztuv& w[hx − 1y
=
=
h
c)0 Ztuv& w[hx − 1y
=
h
d) 0Ztuv& w[hx y
=
For more information log on to www.gateaerospaceforum.com
Page 11
© GATE AEROSPACE FORUM
Q.46) The polytrophic efficiency of the compressor is 85%. If the ideal outlet temperature of the
compressor is twice that of the inlet, then what is the isentropic efficiency of the compressor? (take
t& = 1.4 +,- tT = 1.33)
a)59.6%
b)46.9%
c)84.9%
d)79.4%
Q.47) A satellite in Earth orbit has a semi-major axis of 6,700Km and an eccentricity of 0.01. What is the
satellite’s altitude at perigee?
a)255 Km
b)285 Km
c)225Km
d)315 K
Q.48) the function of trim tab in elevator is
a) To decrease the control power applied by the pilot to the elevator.
b) To increased the control power applied by the pilot to the elevator.
c) No effect on control power .
d) It depends on the gust velocity direction.
Q.49) Dorsal fin gives effective
a) Directional stability at low angle of yaw.
b) Directional stability at high angle of yaw.
c) Longitudinal stability at high angle of yaw.
d) No contribution in directional stability.
For more information log on to www.gateaerospaceforum.com
Page 12
© GATE AEROSPACE FORUM
Q.50) The wing dihedral, which is the angle between the plane of each wing and the horizontal when the
aircraft is unbanked and level and is (+ve) when wing lies above horizontal plane through its root
contributes
a) Stability effect in lateral direction or mode.
b) Unstability effect in lateral direction or mode.
c) No contribution effect in lateral direction or mode.
d)It depends on gust velocity vector.
Common data Question Q.51 and Q.52
Statement:-An axial flow compressor has an overall pressure ratio of 4.0 and mass flow of 3Kg/s. If
the polytropic efficiency is 88% and the stagnation temperature rise per stage must not exceed 25K
Assume equal temperature rise in all stages (Ambient stagnation condition are 1.01 bar,
288K)(Assume t = 1.4)
Q.51) The number of stages are.
a) 8
b) 6
c) 7
d) 5
c) 1.378
d) 1.078
Q.52) The pressure ratio for the last stage is
a) 1.278
b) 1.178
common data type question Q53 and Q54
statement: A planet of mass M has three satellite of equal mass m, each moving in the same circular orbit of
Radius R. satellites are equally spaced and form an equilateral triangle.
Q.53. The total potential Energy of the satellite –Planet system is
(a) U =
(c)r =
`#
|
`
|
(1 +
)
√
(b) U =
(d) r =
(} + √ })
#
(0 +
`
'30 +
|
|
For more information log on to www.gateaerospaceforum.com
√
})
√
}*
Page 13
© GATE AEROSPACE FORUM
Q.54.The orbital speed of each satellite such that they maintain this confrigration is
#
(a) V= (√| −
`
(c) V= (
|
+
` 1/2
)
|
(b) V= (
# 1/2
(d) V= (
√|
)
`
+
`.
− √|)1/2
|
|
# 1/2
√|
)
.#
common data type answer question Q55 & Q56
Statement:
Consider a vortex filament and straight line through the centre of the loop , perpendicular to the
plane of the loop .
Q. 55) The expression for a velocity at a distance A on the line ,as induced by the vortex filament is
where ( Γ is the circulation )
C
I
a) ΓR/2(A + R )
b) ΓRA/2(A + R )
C
I
c) ΓA/2(A + R )
d) ΓR /2(A + R )
Q.56) The velocity at the centre of loop induced by vortex filament is
ƒ
b)| ‚
ƒ
a)0 ‚
Γ
ƒ
c) m| ‚
Γ
ƒ
d) D| ‚
Γ
Linked answer question Q.57 & Q.58
Q.57)The value of L (
M„… &)
)
) is
k
&
b) − tan (&)
k
&
d) + tan (&)
a) + tan ( )
c) − tan ( )
N M„… )
Q.58)JO
k
a) D
)
k
k
dt equal to
b)
k
c)
k
D
k
d) For more information log on to www.gateaerospaceforum.com
Page 14
© GATE AEROSPACE FORUM
Linked answer Question Q59 & 60
A turboprop engine operates at an altitude of 3000 meters above mean sea level and an aircraft speed
of 525 Kmph. The data of the engine is given below:
Inlet diffuse efficiency=0.875
Compressor efficiency=0.790
Velocity of air at compressor entry=90 m/s
Temperature rise through the compressor=230°
Properties of air :t = 1.4, X = 1.005 ‚Œ/‚/Ž
Q.59) what is the pressure rise through the inlet diffuser?(Use above data)
a) 0.0537 bar
b) 0.0837 bar
c) 0.0237 bar
d) 0.1137 bar
Q.60) what is the air standard efficiency of the engine?( use above data)
a) 0.2294
b) 0.3942
c) 0.4429
For more information log on to www.gateaerospaceforum.com
d) 0.6249
Page 15