The flow speeds of air on the lower and upper | vedclass

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(C) According to Bernoulli's principle,for horizontal flow,$P_1 + \frac{1}{2}\rho v_1^2 = P_2 + \frac{1}{2}\rho v_2^2$.Let $P_1$ and $v_1$ be the pres

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$\frac{3}{2}\rho v^2 A$

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(C) According to Bernoulli's principle,for horizontal flow,$P_1 + \frac{1}{2}ho v_1^2 = P_2 + \frac{1}{2}ho v_2^2$.Let $P_1$ and $v_1$ be the pressure and speed on the lower surface,and $P_2$ and $v_2$ be the pressure and speed on the upper surface.Given $v_1 = v$ and $v_2 = 2v$.The pressure difference $\Delta P = P_1 - P_2 = \frac{1}{2}ho(v_2^2 - v_1^2)$.Substituting the values: $\Delta P = \frac{1}{2}ho((2v)^2 - v^2) = \frac{1}{2}ho(4v^2 - v^2) = \frac{1}{2}ho(3v^2) = \frac{3}{2}ho v^2$.The dynamic lift $L$ is the force due to this pressure difference: $L = \Delta P 	imes A$.Therefore,$L = \frac{3}{2}ho v^2 A$.

The flow speeds of air on the lower and upper surfaces of the wing of an aeroplane are $v$ and $2v$ respectively. The density of air is $\rho$ and the surface area of the wing is $A$. The dynamic lift on the wing is:

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