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Air streams horizontally past on air plane wing of area 120m^2 weighing 300 kg.d speed over d top surface is 60m/s and dat under d bottom surface is 45m/s.density of air is 1.293kg/m^3.wat is d lift on d wing.
Pressure difference=Lift force/Surface area or, 1/2ρair(Vtop2-Vbelow2) =F/A Entering all values given in problem in above equation & calculating the lift force F=122.18kN ; or, (lift)accn = 407.3m/s2
Pressure difference=Lift force/Surface area
or, 1/2ρair(Vtop2-Vbelow2) =F/A
Entering all values given in problem in above equation & calculating the lift force F=122.18kN ; or, (lift)accn = 407.3m/s2
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