Flow Field Measurements of Leading-edge Separation Vortex Formed on a Delta Wing with Vortex Flaps

Article type: Research Article

Authors: Rinoie, K.

Affiliations: Department of Aeronautics and Astronautics, The University of Tokyo, Hongo, Tokyo 113-8656, Japan.

Abstract: Wind tunnel tests are carried out using a 70 · delta wing model with leading-edge vortex flaps. The structure of the leading-edge separation vortex over the leading-edge vortex flap is measured by use of a 5 holes pitot probe, surface pressure measurement technique and oil flow visualization technique. Separation vortices formed on a plain delta wing, on a vortex flap and inboard the vortex flap hinge line are clearly visualized. Results indicate that the flow around the vortex flaps is classified into several different cross flow patterns. The streamwise flap deflection angle is defined to discuss the vortex flap performance. The optimum lift to drag ratio is attained when the amount of the wing angle of attack is not far different from that of the streamwise flap deflection angle, as long as the vortex flap is deflected modestly.

Keywords: leading-edge separation vortex, delta wing, cross flow pattern, aircraft performance, vortex flap

Journal: Journal of Visualization, vol. 4, no. 2, pp. 169-178, 2001