Experimental investigations of the flowfield of an airfoil with spoiler

Abstract

An experiment was performed on the flowfields of an airfoil with deflected spoiler at low speed. Surface pressure distributions and boundary-layer and wake profiles were measured systematically to evaluate the effects of angle of attack and spoiler deflection on mean and fluctuating quantities. Boundary-layer and base pressure characteristics were analyzed. The development of wake with angle of attack is hypothesized by the variation of base pressure. The location of hinge bubble depends on boundary-layer characteristics. The wake is self-preserved if a virtual origin is introduced.