Static and total pressure distributions around a thick delta wing with rounded leading edge

Abstract

Tlic flowfield around a thick delta wing with high aspect ratio and rounded leading edge was investigated experimentally. The Velocity field was measured by Laser Doppler Anemometry (LDA), and total pressure distributions by Pitot tube. Further more, static pressure distributions and oilflow pattern on the wing surface were also studied to understand the characteristic features of the thick delta wing. These results were compared wit,h the thin d e l h wing with small rounded leading edge. Although the thick delta wing produces lower lift coefficient than the thin wing a t small anglcs of attack, stall is slightly delayed. This can he explained from the difference in the size of leading edge vortcx; the vortex of the thin delta wing spreads wider than the thick one. Therefore, leading edge vortices coming from the left and right leading edges collide with each other a t lower attack angles in the thin wing, which might lead to stall phenomenon Furthermore, it was found from the LDA measurernent that a high speed region was formed just outside the leading edge vortex. v