抄録
The objective of the present study is to investigate the flow mechanism of delaying stall by use of a wavy leading edge on rectangular wing. Flows around rectangular wings with wavy leading edge were simulated by large eddy simulation with the Dynamic Smagorinsky Model (DSM). The Reynolds number based on the chord length of the wing and the uniform-flow velocity was 1:38X105. The predicted lift and drag coefficients for poststall condition agreed qualitatively with experimental data by using DSM, moreover those for prestall condition were in very good agreement with the experimental data. The mechanism of delaying stall was revealed by the flow simulation. The predicted flows around the wavy leading edge indicated existence of longitudinal vortices and the flows around wavy leading edge remained attached at poststall angle of attack. The longtiudinal vortices were carried to wing tips and the flow separation was suppressed in the area from the protuberances to the wing tips.
