Aerospace Engineering > GATE 2013 > Aircraft Performance
Data for an airplane are given as follows:
weight W = 30 kN,
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 + 0.024CL2.
Assume air density at sea-level ρ∞ = 1.22 kg/m3.
Minimum and maximum speeds of the airplane in level flight condition at sea-level in m/s are respectively
Minimum and maximum speeds of the airplane in level flight condition at sea-level in m/s are respectively
Correct : d
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