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Home » Engineering » Aptitude Test - 115
Hassan
1.When the temperature of air leaving the intercooler, in a two stage compression with intercooler, is __________ the original atmospheric air temperature, then the intercooling is known as perfect or complete intercooling.
A. equal to
B. less than
C. more than
D. equal to
2.The compression ratio in a gas turbine is
A. 4
B. 1
C. 9
D. 4
3.Only rocket engines can be propelled to space because
A. they can generate very high thrust
B. they have high propulsion efficiency
C. these engines can work on several fuels
D. they can generate very high thrust
4.An aftercooler is used to
A. remove impurities from air
B. reduce volume of air
C. cause moisture and oil vapour to drop out
D. remove impurities from air
5.High air-fuel ratio in gas turbines
A. increases power output
B. improves thermal efficiency
C. reduces exhaust temperature
D. increases power output
6.The ratio of the volume of free air delivery per stroke to the swept volume of the piston, is known as
A. compressor efficiency
B. volumetric efficiency
C. isothermal efficiency
D. compressor efficiency
7.The ratio of the indicated power to the shaft power or brake power of the motor or engine required to drive the compressor, is called
A. compressor efficiency
B. volumetric efficiency
C. isothermal efficiency
D. compressor efficiency
8.The type of rotary compressor used in aeroplanes, is of
A. centrifugal type
B. axial flow type
C. radial flow type
D. centrifugal type
9.In a reciprocating air compressor, the compression work per kg of air
A. increases as clearance volume increases
B. decreases as clearance volume increases
C. is independent of clearance volume
D. increases as clearance volume increases
10.The degree of reaction in an axial flow compressor is defined as the ratio of static enthalpy rise in the
A. rotor to static enthalpy rise in the stator
B. stator to static enthalpy rise in the rotor
C. rotor to static enthalpy rise in the stage
D. rotor to static enthalpy rise in the stator
11.Continuous flow of fluid is called as _______
A. Continuum
B. Invincible flow
C. Continuum & Invincible flow
D. Continuum
12.Knudsen number does not have any __________
A. units & dimension
B. units
C. dimension
D. units & dimension
13.Continuum in fluids is predicted by using ________
A. Knudsen number
B. Mach number
C. Knudsen & Mach number
D. Knudsen number
14.Ratio of mean free path to characteristic length is called as _________
A. Mach number
B. Knudsen number
C. Nusselt number
D. Mach number
15.Distance traveled by the molecule in between successive collisions is called as __________
A. mean free path
B. kinetic path
C. mean free path & kinetic path
D. mean free path
16.Knudsen number is less than _______
A. 1
B. 0.5
C. 0.3
D. 1
17.Continuum equations are valid only when Knudsen number is ________ than 0.3.
A. greater
B. less
C. equal
D. greater
18.When altitude of earth is in between 90 km and 150 km Knudsen number can be in between 0.3 and__?
A. 1
B. 2
C. 3
D. 1
19.Knudsen number ranges in between 0.3 and 1 in ________
A. boundary & transient region
B. boundary region
C. transient region
D. boundary & transient region
20.Airfoil when passed through fluids produces ______________
A. thrust
B. drag
C. thrust & drag
D. thrust
21.Air foils when designed to work in water are called as _________
A. Dynamic air foil
B. Hydro foil
C. Dynamic air foil & Hydro foil
D. Dynamic air foil
22.In air foil lift is __________ proportional to angle of attack.
A. inversly
B. not related
C. directly
D. inversly
23.Cambered air foils generate lift at ________ angle of attack.
A. zero
B. high
C. low
D. zero
24._____ difference is observed in between the sides of air foil.
A. Temperature
B. Pressure
C. Temperature & pressure
D. Temperature
25.Relation between angle of attack and _______ for invincible fluids is found in thin airfoil theory.
A. Lift
B. Drag
C. Lift & Drag
D. Lift
26.Slope between lift coefficient and angle of attack in a line is __________
A. 90 degree
B. 180 degree
C. 360 degree
D. 90 degree
27.Center of pressure lies exactly in ________ of the chord from the leading edge in a symmetrical air foil.
A. one quarter
B. half
C. three fourth
D. one quarter
28.Aerodynamic center lies exactly at ______ on the chord from leading edge in cambered air foil.
A. half
B. one quarter
C. three fourth
D. half
29.Cryogenic fuels are stored under _______ temperatures.
A. high
B. low
C. medium
D. high
30.Rocket engines require _______ mass flow rate.
A. high
B. low
C. medium
D. high
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