GATE 2017-2018 :: GATE Aeronautical Engineering
- The critical Mach number for a flat plate of zero thickness, at zero angle of attack, is _________
- A damped single degree-of-freedom system is vibrating under a harmonic excitation with an amplitude ratio of 2.5 at resonance. The damping ratio of the system is ______________
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The channel section of uniform thickness 2mm shown in the figure is subjected to a torque of 10 Nm. If it is made of a material with shear modulus of 25 GPa, the twist per unit length in radians/m is _________
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The stiffened cross-section of a long slender uniform structural member is idealized as shown in the figure below. The lumped areas at A, B, C and D have equal cross-sectional area of 3 cm2. The webs AB, BC, CD and DA are each 5 mm thick. The structural member is subjected to a twisting moment of 10 kNm. The magnitudes of the shear flow in the webs, qAB, qBC, qCD, and qDA in kN/m are, respectively
- Consider two engines P and Q. In P, the high pressure turbine blades are cooled with a bleed of 5% from the compressor after the compression process and in Q the turbine blades are not cooled. Comparing engine P with engine Q, which one of the following is NOT TRUE?
- The mass flow rate of air through an aircraft engine is 10 kg/s. The compressor outlet temperature is 400 K and the turbine inlet temperature is 1800 K. The heating value of the fuel is 42 MJ/kg and the specific heat at constant pressure is 1 kJ/kg-K. The mass flow rate of the fuel in kg/s is approximately ___________
- For a given inlet condition, if the turbine inlet temperature is fixed, what value of compressor efficiency given below leads to the lowest amount of fuel added in the combustor of a gas turbine engine?
- A gas turbine engine is mounted on an aircraft which can attain a maximum altitude of 11 km from sea level. The combustor volume of this engine is decided based on conditions at
- Consider the low earth orbit (LEO) and the geo synchronous orbit (GSO). Then
- Which one of the following shows the CORRECT variation of stagnation temperature along the axis of an ideal ram jet engine?
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A.
∆V requirement for launch to LEO is greater than that for GSO, and altitude of LEO is lower than that of GSO
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B.
∆V requirement for launch to LEO is lower than that for GSO, and altitude of LEO is lower than that of GSO
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C.
∆V requirement for launch to LEO is greater than that for GSO, and altitude of LEO is greater than that of GSO
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D.
∆V requirement for launch to LEO is lower than that for GSO, and altitude of LEO is greater than that of GSO
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