Abstract: The numerical method and experiment technique were conducted to investigate what effect will be produced on the flow structure and aerodynamics over the highly swept delta wing with suction technique in the Lee Side at high angle of attack. Harten Yee's second order TVD scheme and Navier Stokes equations were utilized in numerical simulation. A laser illumination for flow visualization and the strain gauge balance were carried out in experiment. The main result was that through suction in the delta wing Lee Side to reel off the low energy flow, the effect of increasing lift was not satisfied and much more lower than the effect of the two dimensional condition. The reason is the basic difference between the three dimensional separation and the two dimensional separation.

Key words: delta wing, separ ation flow, blowing-suction, vor tex contr ol, flow visualization