GATE 2017-2018 :: GATE Aeronautical Engineering
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Data for an airplane are given as follows: weight W = 30kN, thrust available at sea-level T0 = 4000 N, wing planform area S = 30 m2, maximum lift coefficient CL max = 1.4, and drag coefficient CD = 0.015 + 0.024 C2L. Assume air density at sea-level P∞ = 1.22 kg/ m3. Stall speed of the airplane in m/s is
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Data for an airplane are given as follows: weight W = 30kN, thrust available at sea-level T0 = 4000 N, wing planform area S = 30 m2, maximum lift coefficient CL max = 1.4, and drag coefficient CD = 0.015 + 0.024 C2L. Assume air density at sea-level P∞ = 1.22 kg/ m3. Minimum and maximum speeds of the airplane in level flight condition at sea-level in m/s are respectively
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An aircraft is flying at Mach number M = 1.5, where the ambient temperature is 250 K. The stagnation temperature of gases at the entry to the nozzle is 800 K. The nozzle is choked and always under expanded. Assume the molecular weight of the exhaust gases to be 29, the ratio of specific heats to be 1.4 and the universal gas constant is 8314 J/kmol-K. For which one of the nozzle exit Mach numbers given below is the propulsive efficiency highest?
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An aircraft is flying at Mach number M = 1.5, where the ambient temperature is 250 K. The stagnation temperature of gases at the entry to the nozzle is 800 K. The nozzle is choked and always under expanded. Assume the molecular weight of the exhaust gases to be 29, the ratio of specific heats to be 1.4 and the universal gas constant is 8314 J/kmol-K. For which one of the nozzle exit Mach numbers given below is the thrust highest?
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A wing-body alone configuration airplane with a wing loading of W/S = 1000 N/m2 is flying in cruise condition at a speed V = 90m/s at sea-level (air density at sea-level P∞ = 1.22 kg/m3). The zero lift pitching moment coefficient of the airplane is Cwbmac = Cm0 = -0.06 and the location of airplane aerodynamic center from the wing leading edge is Xac = 0.25c. Here c is the chord length. The airplane trim lift coefficient CL trim is
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A wing-body alone configuration airplane with a wing loading of W/S = 1000 N/m2 is flying in cruise condition at a speed V = 90m/s at sea-level (air density at sea-level P∞ = 1.22 kg/m3). The zero lift pitching moment coefficient of the airplane is Cwbmac = Cm0 = -0.06 and the location of airplane aerodynamic center from the wing leading edge is Xac = 0.25c. Here c is the chord length. Distance of center of gravity of the aircraft (XCG) from the wing leading edge is
- If 3 ≤ X ≤ 5 and 8 ≤ Y ≤ 11 then which of the following options is TRUE?
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The Headmaster ___________ to speak to you. Which of the following options is incorrect to complete the above sentence?
- Mahatama Gandhi was known for his humility as
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All engineering students should learn mechanics, mathematics and how to do computation. I II III IVWhich of the above underlined parts of the sentence is not appropriate?
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