GATE Aeronautical Engineering - GATE 2017-2018 Questions and Answers

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Discussion :: GATE Aeronautical Engineering

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 C_{L max} = 1.4, and drag coefficient C_D = 0.015 + 0.024 C²_L. Assume air density at sea-level P_âˆž = 1.22 kg/ m³.

Minimum and maximum speeds of the airplane in level flight condition at sea-level in m/s are respectively

17.36 and 180

17.36 and 34.22

34.22 and 119.46

17.36 and 119.46

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