Ideal flow theory will yield a flow pattern past an airfoil similar to that shown. If the approach air velocity V₀ is 80 m/s, what is the pressure difference between the bottom and the top of this airfoil at points where the velocities are V₁ = 85 m/s and V₂ = 75 m/s? Assume ρair is uniform at 1.2 kg/m³.

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V. V2