An airplane in level flight whose mass is 20,000 kg has a wing area of 60 m2. What is the pressure difference between the upper and lower surfaces of its wing?
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weight = pressure difference * area of wings. Weight = mass * g = 20,000 kg * 10 m/s² = 200,000 N. So, ΔP = 200,000/60 N/m² = 10,000/3 N/m² = 3,333.33 N/m² or 3,333.33 Pa.
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