The velocity induced by the thickness of a thin infinite wing in a parallel flow can be calculated, at some distance from the wing, by linearized subsonic compressible flow theory. If now, a portion of the infinite wing is removed from the flow, the velocity at any point on the wing will be less by the velocity induced by the portion of the wing which was removed. Furthermore, if the part removed is relatively far away from the point on the wing for which the induced velocity is being calculated, linearized subsonic compressible flow theory is valid. Utilizing such a scheme, the velocity at the location of a finite wing can be considered as being the same as for the infinite wing, reduced by the amount which would have been contributed by the portions of the infinite wing which were removed from the flow. The difference in the induced velocity can be averaged over the area of the finite wing and the average applied as a correction to the free-stream velocit}^. At this increased freestream velocity, the finite wing should have approximately the same pressure distribution as the infinite wing at the uncorrected free-stream velocity.