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Rotor wake vortex interaction causes flow separation on the upper surface of a Lifting surface a t low angles of attack, where the time-averaged flow would be expected to remain fully attached. This phenomenon is studied using a full-scale UH-1 stabilator and a two bladed teetering rotor in a wind tunnel. A large once-per-rev pressure fluctuation is observed. Strong time-averaged spanwise flow is observed downstream of the unsteady separation line. The vortex interaction effect decreases with increasing advance ratio. These results are insensitive to small perturbations of the flowAeld caused by movement of a small lifting surface upstream.