Pressure Difference on an airplane wing

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To find the pressure difference on an airplane wing, Bernoulli's principle is applied, which states that an increase in the speed of a fluid occurs simultaneously with a decrease in pressure. Given the airspeed over the upper surface is 128 m/s and the lower surface is 105 m/s, the pressure difference can be calculated using the equation P1 + 0.5ρv1² = P2 + 0.5ρv2², where ρ is the air density. The net upward force on the wing can then be determined by multiplying the pressure difference by the wing area of 26 m². This calculation reveals the lift generated by the wing due to the varying airspeeds above and below it. Understanding these principles is crucial for analyzing aerodynamic forces on aircraft.
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Find the pressure difference on an airplane wing where air flows over the upper surface with a speed of 128 m/s, and along the bottom surface with a speed of 105 m/s.

If the area of the wing is 26 m2, what is the net upward force exerted on the wing?
 
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I am totally stuck on this one.. I don't even know where to begin...
 

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