Derive an expression for the load distribution

Reference no: EM131515204

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

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

Reference no: EM131515204

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