A three-dimensional wind-tunnel test of a circulation control wing has been performed. The data obtained indicated that the section characteristics for the wing may be approximated from two-dimensional data, even in the presence of wing sweep and finite span. No first-order effects of sweep were apparent in the degree of mixing between the trailing-edge jet and the upper surface boundary layer. The finite extent of the trailing-edge jet was shown to introduce additional contributions to the downwash distribution along the span in response to the vorticity shed at the jet extremities.