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Engineering GATE 2017-2018 Aeronautical

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1. The constraint A2 = A on any square matrix A is satisfied for




2. The general solution of the different equation d2y/dt2 + dy/dt - 2t = 0 is




3. An aircraft in trimmed condition has zero pitching moment at




4. In an aircraft, constant roll rate can be produced using ailerons by applying




5. For a symmetric airfoil, the lift coefficient for zero degree angle of attack is




6. The critical Mach number of an airfoil is attained when




7. The shadowgraph flow visualization technique depends on




8. The Hohmann ellipse used as earth-Mars transfer orbit has




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




10. The Poisson's ratio,ν of most aircraft grade metallic alloys has values in the range:




11. The value of k for which the system of equations x + 2y + kz =1; 2x + ky +8z = 3 has no solution is




12. If u(t) is a unit step function, the solution of the differential equation m d2x/dt2 + kx = u(t) in Laplace domain is




13. The general solution of the differential equation dy/dx - 2√y = 0 is




14. During the ground roll manoeuvre of an aircraft, the force(s) acting on it parallel to the direction of motion




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




16. In an aircraft, the dive manoeuvre can be initiated by




17. In an aircraft, elevator control effectiveness determines




18. The Mach angle for a flow at Mach 2.0 is




19. Bernoulli's equation is valid under steady state




20. The ratio of flight speed to the exhaust velocity for maximum propulsion efficiency is




21. The ideal static pressure coefficient of a diffuser with an area ratio of 2.0 is




22. 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




23. In a semi-monocoque construction of an aircraft wing, the skin and spar webs are the primary carriers of




24. 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




25. 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 ____.




26. 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 ____.




27. 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 ____.




28. The mode shapes of an un-damped two degrees of freedom system are {1 0.5 } T and {1 -0.675 } T . 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 ____.




29. The nth derivative of the function y = 1/(x + 3) is




30. The volume of a solid generated by rotating the region between semi-circle y = 1 − √1− x2 and straight line y = 1, about x axis, is




31. If an aircraft takes off with 10% less fuel in comparison to its standard configuration, its range is




32. 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




33. An oblique shock wave with a wave angle β is generated from a wedge angle of θ. The ratio of the Mach number downstream of the shock to its normal component is




34. 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




35. 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




36. 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




37. 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?




38. A bipropellant liquid rocket motor operates at a chamber pressure of 40 bar with a nozzle throat diameter of 50 mm. The characteristic velocity is 1540 m/s. If the fuel-oxidizer ratio of the propellant is 1.8, and the fuel density is 900 kg/m3, what should be the minimum fuel tank volume for a burn time of 8 minutes




39. The propellant in a single stage sounding rocket occupies 60% of its initial mass. If all of it is expended instantaneously at an equivalent exhaust velocity of 3000 m/s, what would be the altitude attained by the payload when launched vertically? [Neglect drag and assume acceleration due to gravity to be constant at 9.81 m/s2.]




40. The Airy stress function, φ =α x2 +β xy +γ y2 for a thin square panel of size l ×l automatically satisfies compatibility. If the panel is subjected to uniform tensile stress, σo on all four edges, the traction boundary conditions are satisfied by




41. The boundary condition of a rod under longitudinal vibration is changed from fixed-fixed to fixedfree. The fundamental natural frequency of the rod is now k times the original frequency, where k is




42. A spring-mass system is viscously damped with a viscous damping constant c. The energy dissipated per cycle when the system is undergoing a harmonic vibration X Cosωdt is given by




43. Buckling of the fuselage skin can be delayed by




44. A wing and tail are geometrically similar, while tail area is one-third of the wing area and distance between two aerodynamic centres is equal to wing semi-span (b/2). In addition, following data is applicable: ∈α = 0.3, CL = 1.0, CLα 0.08/ deg., c = 2.5 , b = 30m , CMac = 0, ηt = 1. The symbols have their usual aerodynamic interpretation. The maximum distance that the centre of gravity can be behind aerodynamic centre without destabilizing the wing-tail combination is




45. A wing and tail are geometrically similar, while tail area is one-third of the wing area and distance between two aerodynamic centres is equal to wing semi-span (b/2). In addition, following data is applicable: ∈α = 0.3, CL = 1.0, CLα 0.08/ deg., c = 2.5 , b = 30m , CMac = 0, ηt = 1. The symbols have their usual aerodynamic interpretation. The angle of incidence of tail to trim the wing-tail combination for a 5% static margin is




46. A thin long circular pipe of 10 mm diameter has porous walls and spins at 60 rpm about its own axis. Fluid is pumped out of the pipe such that it emerges radially relative to the pipe surface at a velocity of 1 m/s. [Neglect the effect of gravity.] What is the radial component of the fluid's velocity at a radial location 0.5 m from the pipe axis?




47. A thin-walled spherical vessel (1 m inner diameter and 10 mm wall thickness) is made of a material with |σY| = 500MPa in both tension and compression. The internal pressure pY at yield, based on the von Mises yield criterion, if the vessel is floating in space, is approximately




48. A thin-walled spherical vessel (1 m inner diameter and 10 mm wall thickness) is made of a material with |σY| = 500MPa in both tension and compression. If the vessel is evacuated (internal pressure = 0) and subjected to external pressure, yielding according to the von Mises yield criterion (assuming elastic stability until yield)




49. Choose the most appropriate alternative from the options given below to complete the following sentence: I ___ to have bought a diamond ring.




50. Choose the most appropriate alternative from the options given below to complete the following sentence: Food prices ___ again this month.




51. Choose the most appropriate alternative from the options given below to complete the following sentence: The administrators went on to implement yet another unreasonable measure, arguing that the measures were already ___ and one more would hardly make a difference.




52. Choose the most appropriate alternative from the options given below to complete the following sentence: To those of us who had always thought him timid, his ___ came as a surprise.




53. The arithmetic mean of five different natural numbers is 12. The largest possible value among the numbers is




54. If a prime number on division by 4 gives a remainder of 1, then that number can be expressed as




55. Two points (4, p) and (0, q) lie on a straight line having a slope of 3/4. The value of (p “ q) is




56. In the early nineteenth century, theories of social evolution were inspired less by Biology than by the conviction of social scientists that there was a growing improvement in social institutions. Progress was taken for granted and social scientists attempted to discover its laws and phases. Which one of the following inferences may be drawn with the greatest accuracy from the above passage? Social scientists