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- Question 1 of 17
Combustion in gas turbine engines is ideally represented as the following processCorrectIncorrect
- Question 2 of 17
For a given chamber pressure, the thrust of a rocket engine is highest whenCorrectIncorrect
- Question 3 of 17
The damping ratio in phugoid motion for gliders is usually less compared to powered aircraft becauseCorrectIncorrect
- Question 4 of 17
During an aircraft cruising flight, the altitude above the ground is usually measured usingCorrectIncorrect
- Question 5 of 17
Indicated airspeed is used by a pilot duringCorrectIncorrect
- Question 6 of 17
The pitch angle and the angle of attack for a fixed wing aircraft are equal duringCorrectIncorrect
- Question 7 of 17
The load factor of an aircraft turning at a constant altitude is 2. The coefficient of lift required for turning flight as compared to level flight at the same speed will beCorrectIncorrect
- Question 8 of 17
An un-mixed turbofan engine with a bypass ratio of 6.0, flies with a velocity of 200 m/s. The core and the bypass nozzles of the engine, that are both convergent nozzles, operate under choked condition and have exhaust static temperatures of 580 K and 295 K, respectively. The specific gas
constant and the ratio of specific heats for both the streams are 287 J/kgK and 1.4, respectively. If the fuel-air ratio is negligible, the thrust per unit mass flow rate generated by the engine is _______Ns/kg.CorrectIncorrect
- Question 9 of 17
A single-stage gas turbine operates with an axial absolute flow at the entry and exit from the stage. The absolute flow angle at the nozzle exit is 70 degree. The turbine stage generates a specific work of 228 kJ/kg when operating with a mean blade speed of 440 m/s. The absolute velocity at the rotor
- Question 10 of 17
An axial compressor operates such that it has an inlet and an exit total temperature of 300 K and 430 K, respectively. The isentropic efficiency of the compressor is 85 %. If the ratio of specific heats is 1.4, then the total pressure ratio across the compressor isCorrectIncorrect
- Question 11 of 17
The maximum value of coefficient of lift (Cl) for a 2D circular cylinder, provided at least one stagnation point lies on the cylinder surface, is predicted by the potential flow theory to beCorrectIncorrect
- Question 12 of 17
A gaseous mixture of air and fuel enters a constant area combustion chamber at a velocity of 100 m/s and at a static temperature of 300 K. The heat release due to combustion is 1000 kJ/kg. The specific heat at constant pressure of the calorically perfect gas is 1000 J/kgK. The total temperature of air-fuel mixture after combustion is ______ KCorrectIncorrect
- Question 13 of 17
A launch vehicle has a main rocket engine with two identical strap-on motors, all of which fire simultaneously during the operation. The main engine delivers a thrust of 6300 kN with a specific impulse of 428 s. Each strap-on motor delivers a thrust of 12000 kN with specific impulse of 292 s.The acceleration due to gravity is 9.81 m/s2 . The effective (combined) specific impulse of the vehicle is _______ sCorrectIncorrect
- Question 14 of 17
A substance experiences an entropy change of s > 0 in a quasi-steady process. The rise in temperature (corresponding to the entropy change s) is highest for the following process:CorrectIncorrect
- Question 15 of 17
In a particular rocket engine, helium propellant is heated to 6000 K and 95% of its total enthalpy is recovered as kinetic energy of the nozzle exhaust. Consider helium to be a calorically perfect gas with specific heat at constant pressure of 5200 J/kgK. The exhaust velocity for such a rocket for an
optimum expansion is _____ m/s.CorrectIncorrect
- Question 16 of 17
An aircraft weighing 10000 N is flying level at 100 m/s and it is powered by a jet engine. The thrust required for level flight is 1000 N. The maximum possible thrust produced by the jet engine is 5000 N. The minimum time required to climb 1000 m, when flight speed is 100 m/s, is ________s.CorrectIncorrect
- Question 17 of 17
A rocket, with a total lift-off mass of 10000 kg, moves vertically upward from rest under a constant gravitational acceleration of 9.81 m/s2 . The propellant mass of 8400 kg burns at a constant rate of 1200 kg/s. If the specific impulse of the rocket engine is 240 s, neglecting drag, the burnout
velocity in m/s isCorrectIncorrect