Abstract:
The problem of the incompressible potential flow past a conventional aerofoil which has an arbitrary distribution of normal velocity
across its surfaoe is solved by the application of conformal transformation to the solution derived for the corresponding problem for the unit circle.
Several simple worked examples are given. Although it is theoretically possible to obtain any desired tangential velocity distribution on an aerofoil by the correct choice of suction velocity distribution, and this use of "sink effect" gives promise of considerable lift increments, it is considered that the quantities of suction required to produce such desired affects are prohibitively large for inmediate practical use. For suction quantities of the order of those at which boundary-layer porous suction is designed to act, the effect of the solution on the main stream potential flow is negligible.
