Derive an expression for the load distribution pressure


Question: The camber line of a circular-arc airfoil is given by

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Derive an expression for the load distribution (pressure difference across the airfoil) at incidence α. Show that the zero-lift angle αo = -2h, and sketch the load distribution at this incidence. Compare the lift curve of this airfoil with that of a flat plate.

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Physics: Derive an expression for the load distribution pressure
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