Inviscid and Viscous Interactions in Subsonic Corner Flows

Abstract

A flap can be used as a high-lift device, in which a downward deflection results in a gain in lift at a given geometric angle of attack. To characterize the aerodynamic performance of a deflected surface in compressible flows, the present study examines a naturally developed turbulent boundary layer past the convex and concave corners. This investigation involves the analysis of mean and fluctuating pressure distributions. The results obtained indicate strong inviscid-viscous interactions. There are upstream expansion and downstream compression for the convex-corner flows, while the opposite trend is observed for the concave-corner flows. A combined flow similarity parameter, based on the small perturbation theory, is proposed to scale the flow characteristics in both subsonic convex- and concave-corner flows.

Shock Excursion in Transonic Convex-Corner Flows

“…Deflected control surfaces can also be employed in combination to provide variable-camber control during cruise flight 1 . In the previous studies [2][3][4][5][6][7][8][9] , a sharp convex corner was adopted as an idealized configuration that models the deflection of an upper control surface. However, the presence of a short region of convex surface curvature would affect the flow structure, e.g., upstream expansion, downstream compression, shock-induced, boundary-layer separation and flow unsteadiness.…”