Abstract: The flow around a slender was fixed in this way which a tiny pert urbation was located on the nose of the slender. The influence on flow str u cture and aerodynamic of a slender by sweep wing at high angle of attack was studied. The experimental results indicate that at angle of attack 30°,the fl ow and pressure distribution of mid-part leeside of a slender are dominated by sweep wing and forebody vortices. At angles of attack α=40°~60°, sweep wing dominates the flow around the mid-part of a slender only, and the flow of mid-p art leeside of a slender becomes full separate flow, the pressure distribution o f mid-part leeside of a slender retains constant.