Question: The camber line of a circular-arc airfoil is given by
![326_xc.png](https://secure.tutorsglobe.com/CMSImages/326_xc.png)
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.