Study Material from Hal Management Trainee Exam

I am preparing from the Hindustan Aeronautics Limited HAL Management Trainee so can you please provide me the exam pattern, syllabus and the other study material of HAL Management Trainee exam? also suggest me the best books from the preparation of this exam?

Hii Guys , Here will you please provide me Previous year Hal Management Trainee placement Exam paper for exam Preparation ?

[Raman Vij]

Friend have a look , For your help Here I am providing Previous year Hal Management Trainee placement Exam 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. -Answer
(D) no square matrix A.


Q.3 An aircraft in trimmed condition has zero pitching moment at
(A) its aerodynamic centre.
(B) its centre of gravity.-Answer
(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.-Answer

Q.5 For a symmetric airfoil, the lift coefficient for zero degree angle of attack is
(A) – 1.0
(B) 0.0 -Answer
(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.-Answer
(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 spatialcoordinate.-Answer
(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. -Answer
(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.-Answer
(C) 2nd order linear non-homogenous ordinary differential equation.
(D) 4th order nonlinear homogenous ordinary differential equation.

Q.10 The Poisson’s ratio,? of most aircraft grade metallic alloys has values in the range:
(A) -1 =? =0
(B) 0 =? =0.2
(C) 0.2 =? =0.4 -Answer
(D) 0.4 =? =0.5

Q.11 The value of k for which the system of equations x + 2y + kz =1; 2x + ky +8z = 3 has no solution is
(A) 0
(B) 2
(C) 4 -Answer
(D) 8

Q.14 During the ground roll manoeuvre of an aircraft, the force(s) acting on it parallel to the direction of motion
(A) is thrust alone.
(B) is drag alone.
(C) are both thrust and drag.
(D) are thrust, drag and a part of both weight and lift.-Answer

Q.15 An aircraft in a steady climb suddenly experiences a 10% drop in thrust. After a new equilibrium is reached at the same speed, the new rate of climb is
(A) lower by exactly 10%.
(B) lower by more than 10%.-Answer
(C) lower by less than 10%.
(D) an unpredictable quantity.

Q.16 In an aircraft, the dive manoeuvre can be initiated by
(A) reducing the engine thrust alone.
(B) reducing the angle of attack alone.
(C) generating a nose down pitch rate. -Answer
(D) increasing the engine thrust alone.

Q.17 In an aircraft, elevator control effectiveness determines
(A) turn radius.
(B) rate of climb.
(C) forward-most location of the centre of gravity.-Answer
(D) aft-most location of the centre of gravity.

Q.18 The Mach angle for a flow at Mach 2.0 is
(A) 30o -Answer
(B) 45o
(C) 60o
(D) 90o

Q.20 Bernoulli’s equation is valid under steady state
(A) only along a streamline in inviscid flow, and between any two points in potential flow.-Answer
(B) between any two points in both inviscid flow and potential flow.
(C) between any two points in inviscid flow, and only along a streamline in potential flow.
(D) only along a streamline in both inviscid flow and potential flow.

Q.21 The ratio of flight speed to the exhaust velocity for maximum propulsion efficiency is
(A) 0.0
(B) 0.5
(C) 1.0 -Answer
(D) 2.0

Q.22 The ideal static pressure coefficient of a diffuser with an area ratio of 2.0 is
(A) 0.25
(B) 0.50
(C) 0.75
(D) 1.0

Q.23 A rocket is to be launched from the bottom of a very deep crater on Mars for earth return. The specific impulse of the rocket, measured in seconds, is to be normalized by the acceleration due to
gravity at
(A) the bottom of the crater on Mars.
(B) Mars standard “sea level”.
(C) earth’s standard sea level. -Answer
(D) the same depth of the crater on earth.

Q.24 In a semi-monocoque construction of an aircraft wing, the skin and spar webs are the primary carriers of
(A) shear stresses due to an aerodynamic moment component alone.
(B) normal (bending) stresses due to aerodynamic forces.
(C) shear stresses due to aerodynamic forces alone.
(D) shear stresses due to aerodynamic forces and a moment component.-Answer


Q.25 The logarithmic decrement measured for a viscously damped single degree of freedom system is 0.125. The value of the damping factor in % is closest to
(A) 0.5
(B) 1.0
(C) 1.5
(D) 2.0-Answer

Q.27 An aircraft has a steady rate of climb of 300 m/s at sea level and 150 m/s at 2500 m altitude. The time taken (in sec) for this aircraft to climb from 500 m altitude to 3000 m altitude is ____.
Answer 13 to 14

Q.28 An airfoil generates a lift of 80 N when operating in a freestream flow of 60 m/s. If the ambient pressure and temperature are 100 kPa and 290 K respectively (specific gas constant is 287 J/kg-K),
the circulation on the airfoil in m2/s is ____.
Answer 1.1 to 1.2

Q.29 A rocket motor has combustion chamber temperature of 2600 K and the products have molecular weight of 25 g/mol and ratio of specific heats 1.2. The universal gas constant is 8314 J/kg-mole-K.
The value of theoretical c* (in m/s) is ____.
Answer-1430 to 1440

Q.30 The mode shapes of an un-damped two degrees of freedom system are { } 1 0.5T and { } 1 0.675T - . The corresponding natural frequencies are 0.45 Hz and 1.2471 Hz. The maximum amplitude (in mm) of vibration of the first degree of freedom due to an initial displacement of
{2 1}T (in mm) and zero initial velocities is ____.
Answer-2

Q.36 An aircraft is trimmed straight and level at true air speed (TAS) of 100 m/s at standard sea level(SSL). Further, pull of 5 N holds the speed at 90 m/s without re-trimming at SSL (air density = 1.22
kg/m3). To fly at 3000 m altitude (air density = 0.91 kg/m3) and 120 m/s TAS without re-trimming,the aircraft needs
(A) 1.95 N upward force.
(B) 1.95 N downward force.-Answer
(C) 1.85 N upward force.
(D) 1.75 N downward force.

Q.37 An oblique shock wave with a wave angle ß is generated from a wedge angle of ?. The ratio of the Mach number downstream of the shock to its normal component is
(A) sin(ß–?) -Answer
(B) cos(ß–?)
(C) sin(?–ß)
(D) cos(?–ß)

Q.38 In a closed-circuit supersonic wind tunnel, the convergent-divergent (C-D) nozzle and test section are followed by a C-D diffuser to swallow the starting shock. Here, we should have the
(A) diffuser throat larger than the nozzle throat and the shock located just at the diffuser throat.
(B) diffuser throat larger than the nozzle throat and the shock located downstream of the diffuser throat.-Answer
(C) diffuser throat of the same size as the nozzle throat and the shock located just at the diffuser throat.
(D) diffuser throat of the same size as the nozzle throat and the shock located downstream of the diffuser throat.

Q.39 A vortex flowmeter works on the principle that the Strouhal number of 0.2 is a constant over a wide range of flow rates. If the bluff-body diameter in the flowmeter is 20 mm and the piezo-electric transducer registers the vortex shedding frequency to be 10 Hz, then the velocity of the flow would be measured as
(A) 0.1 m/s
(B) 1 m/s -Answer
(C) 10 m/s
(D) 100 m/s

Q.40 The stagnation temperatures at the inlet and exit of a combustion chamber are 600 K and 1200 K, respectively. If the heating value of the fuel is 44 MJ/kg and specific heat at constant pressure for air and hot gases are 1.005 kJ/kg.K and 1.147 kJ/kg.K respectively, the fuel-to-air ratio is
(A) 0.0018
(B) 0.018 -Answer
(C) 0.18
(D) 1.18

Q.41 A solid propellant of density 1800 kg/m3 has a burning rate law r = 6.65 x 10-3p0.45 mm/s, where p is pressure in Pascals. It is used in a rocket motor with a tubular grain with an initial burning area
of 0.314 m2. The characteristic velocity is 1450 m/s. What should be the nozzle throat diameter to achieve an equilibrium chamber pressure of 50 bar at the end of the ignition transient?
(A) 35 mm
(B) 38 mm -Answer
(C) 41 mm
(D) 45 mm