The method of relating the solution of a flow field to the solution of a simpler or known boundary-value problem is extended, subject to edge corrections for finite plan forms, to the most general type of prescribed boundary conditions on a wing in the linearized potential field at subsonic and supersonic speeds. The general procedure for determining edge corrections is given specific "correspondence formulas" are developed for rectangular wings at subsonic and supersonic speeds for cases that do not require the solution of an integral equation.