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- Question 1 of 15
A cruise missile with an ideal ramjet engine is flying at Mach 4.0 at an altitude where the ambient temperature is 100K. Consider ratio of specific heatsγ = 1.4 and specific gas constant R = 287J/kgK.If the stagnation temperature in the combustion chamber is equal to 2310K, the speed of the exhaust gases (in m/s) isCorrectIncorrect
- Question 2 of 15
A gas turbine engine is operating under the following conditions:
Stagnation temperature at turbine inlet 1350 K
Stagnation pressure at the turbine inlet 10 bar
Static temperature at turbine exit 800 K
Velocity at turbine exit 200 m/s
Total-to-total efficiency of turbine 0.96
γ (ratio of specific heats) 1.33
CP(specific heat at constant pressure) 1.147 kJ/kgK
The stagnation pressure (in bar) in the nozzle (considering isentropic nozzle) is equal toCorrectIncorrect
- Question 3 of 15
Air at a stagnation temperature of 300K (ratio of specific heats, γ = 1.4 and specific gas constant R = 287 J/kgK) enters the impeller of a centrifugal compressor in axial direction. The stagnation pressure ratio between the diffuser outlet and impeller inlet is 4.0. The impeller blade radius is 0.3
m and it is rotating at 15000 rev/min. If the slip factor σ (Ratio of tangential component of air velocity at the blade tip to the blade tip speed) is 0.88, the overall efficiency (total-to-total) of the compressor (in %) isCorrectIncorrect
- Question 4 of 15
A stationary two stage rocket with initial mass of 16000kg, carrying a payload of 1000kg, is fired in a vertical trajectory from the surface of the earth. Both the stages of the rocket have same specific impulse, Isp, of 300s and same structural coefficient of 0.14. The acceleration due to gravity is
9.8m/s2. Neglecting drag and gravity effects and considering both the stages with same payload ratio, the terminal velocity attained by the payload in m/s isCorrectIncorrect
- Question 5 of 15
An aircraft is flying at Mach 3.0 at an altitude where the ambient pressure and temperature are 50 kPa and 200 K respectively. If the converging-diverging diffuser of the engine (considered isentropic with ratio of specific heats, γ = 1.4 and specific gas constant R = 287 J/kgK) has a throat area of 0.05 m2, the mass flow rate through the engine in kg/s isCorrectIncorrect
- Question 6 of 15
A cryogenic rocket has a specific impulse of 455s and characteristic velocity of 2386 m/s. The value of thrust coefficient for this rocket isCorrectIncorrect
- Question 7 of 15
For a given airplane with a given wing loading executing a turn in the vertical plane, under what conditions will the turn radius be minimum and the turn rate be maximum?CorrectIncorrect
- Question 8 of 15
Which of the following design parameters influence the maximum rate-of-climb for a jet-propelled airplane?
P. Wing loading
Q. Maximum thrust-to-weight
R. Zero-lift drag coefficient
S. Maximum lift-to-drag ratioCorrectIncorrect
- Question 9 of 15
An aircraft in trimmed condition has zero pitching moment atCorrectIncorrect
- Question 10 of 15
In an aircraft, constant roll rate can be produced using ailerons by applyingCorrectIncorrect
- Question 11 of 15
For a symmetric airfoil, the lift coefficient for zero degree angle of attack isCorrectIncorrect
- Question 12 of 15
The critical Mach number of an airfoil is attained whenCorrectIncorrect
- Question 13 of 15
The shadow graph flow visualization technique depends onCorrectIncorrect
- Question 14 of 15
The Hohmann ellipse used as earth-Mars transfer orbit hasCorrectIncorrect
- Question 15 of 15
The governing equation for the static transverse deflection of a beam under an uniformly distributed load, according to Euler-Bernoulli (engineering) beam theory, is aCorrectIncorrect