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A vortex flowmeter works on the principle that the Strouhal number of 0.2 is a constant over a wide range of flow rates GATE-Aerospace Engineering-Question-20121 AnswerAn airfoil generates a lift of 80 N when operating in a freestream flow of 60 m/s . GATE-Aerospace Engineering-Question-20121 AnswerT he inviscid flow past a rotating circular cylinder can be generated by the superposition of0 AnswerThe Mach angle for a flow at Mach 2.0 is GATE-Aerospace Engineering-Question-20121 AnswerIf an aircraft takes off with 10% less fuel in comparison to its standard configuration, its range is GATE-Aerospace Engineering-Question-20121 AnswerBernoulli’s equation is valid under steady state GATE-Aerospace Engineering-Question-20121 AnswerThe Poisson’s ratio,ν of most aircraft grade metallic alloys has values in the range: GATE-Aerospace Engineering-Question-20121 AnswerIn an aircraft, constant roll rate can be produced using ailerons by applying GATE-Aerospace Engineering-Question-20121 AnswerConsider a 20degree half-angle wedge in a supersonic flow at Mach 3.0 at standard sea-level conditions. If the shock-wave angle on the wedge is 36degreee, the Mach number of the tangential component of the flow post-shock is _______ (accurate to two decimal places). (GATE-Aerospace-Engineering-2018)0 AnswerIf a prime number on division by 4 gives a remainder of 1, then that number can be expressed as GATE-Aerospace Engineering-Question-20121 AnswerThe shadowgraph flow visualization technique depends on GATE-Aerospace Engineering-Question-20121 AnswerT wo packed towers are designed for the same mass velocity of the gas. The first has liquid and gas flow rates of 30 kg/s and 1.2 kg/s, respectively, while the corresponding flow rates in the second tower are 67.5 kg/s and 1.8 kg/s. The ratio of the design diameter of the wider tower to that of the narrower tower is0 AnswerT wo packed towers are designed for the same mass velocity of the gas. The first has liquid and gas flow rates of 30 kg/s and 1.2 kg/s, respectively, while the corresponding flow rates in the second tower are 67.5 kg/s and 1.8 kg/s. The ratio of the design diameter of the wider tower to that of the narrower tower is0 AnswerThe stagnation temperatures at the inlet and exit of a combustion chamber are 600 K and 1200 K, respectively GATE-Aerospace Engineering-Question-20121 AnswerAir at 50 kPa pressure and 400 K temperature flows in a duct at Mach 3.0. A part of the flow leaks through an opening on the duct wall into the ambient, where the pressure is 30 kPa. The maximum Mach number achieved in the discharge is _______ (accurate to two decimal places). (Ratio of specific heats of air is 𝛾=1.4). (GATE-Aerospace-Engineering-2018)0 AnswerT he elementary second-order liquid phase reaction A + B → C + D is carried out in an isothermal plug flow reactor of 2 m3 volume. The inlet volumetric flow rate is 10 m3/h. The initial concentrations of both A and B are 2 kmol/m3. The rate constant is given as 2.5 m3 kmol-1 h-1. The percentage conversion of A is ____________.0 AnswerI f 2 2 2( ) u x y and v axy represent the x- and y-components of the two-dimensional velocity field of an incompressible flow, the value of the constant a is ______0 AnswerAn oblique shock wave with a wave angle β is generated from a wedge angle of θ GATE-Aerospace Engineering-Question-20121 AnswerA 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. GATE-Aerospace Engineering-Question-20121 AnswerAn aircraft has a steady rate of climb of 300 m/s at sea level and 150 m/s at 2500 m altitude. GATE-Aerospace Engineering-Question-20121 Answer
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