Effect of nose thickness distribution on the stall characteristics of low aspect ratio flying wing configuration at transonic flow

Abstract

The wing wing-body thickness of the highly swept flying wing configuration has great influence on the shock-leading edge vortex interaction at transonic speed, which would make significant effect on the stall characteristics. The effects of the nose thickness on the stall characteristics and heading characteristic of the low aspect ratio flying wing configuration are analyzed in simulated method and the flow mechanism is also studied. The results show that to decrease the nose thickness would make the position of the first shock wave and the breakdown position move back and the shock-leading edge vortex interaction will be weakened. To make the nose move back 10% c , the first shock wave in the leeward side will move back and it can delay the vortex breakdown by an angle 4°, which makes the stall angle and available lift coefficient increase. It would significantly improve the stall characteristics and the pitching moment characteristics. To decrease the thickness in nose also can make the heading static instability margin which would improve the heading performance. This study is useful reference for the layout design and flow mechanism of the low aspect flying wing configuration.