A Boeing 747-8I aircraft has a mass of 447,700 kg. This includes loading. The combined area of both wings is 554 m2. The cruising speed is M0.855 (917 km / h). Determine the speed of the wind above the wing to maintain the aircraft's lift. The air density is 1.29 kg / m3
Calculate the required pressure difference () in above and below of the wing to maintain the weight of the aircraft,
ΔP = F/A
= mg/A
= (447700*9.81)/554
= 7927.68 N/m^2
Now Apply Burnolli's equation on above and below of the wings,
ΔP= 1/2*ρ*(v1^2 - v2^2)
v1^2 - v2^2 = (2*ΔP)/ρ
v1^2 = v2^2 + (2*ΔP)/ρ
Substitute the given values values,
v1^2 = (917*5/18)^2 + (2* 7927.68)/1.29
= 648834.41 + 12290.98
v1 = 813.1 m/s
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