带边条后掠翼融合体隐身布局的应用研究

应用棱边边条和小展弦比大后抗角机翼融合设计，使边条涡稳定机头的脱体涡改善机翼根部流场；同时合理配置前翼，使鸭翼产生的涡流流经机翼时，加强了机翼上表面的主体涡流强度，推迟了机翼表面流态分离，提高了机翼的非线性升力。特别在大攻角时，边条涡处在机翼上表面与鸭翼自由涡和机翼主体涡相干涉，形成了三涡一体的非线性升力，极大地改善了全机的流动特性。经实验证明，该布局提供的方案，具有与同类普通布局为高的升力线斜率、高升阻比、大失速攻角及良好的纵横向和侧向静安定性等优点，同时通过电磁模型在微波暗室中测试，在迎头和侧向的ＲＣＳ值（雷达反射截面）均有明显的下降。

A STUDY OF STEALTH LAYOUT FOR A BLENDED WING BODY WITH STREAK

This paper present a new design of a pilotless aircraft with good performance of both aerodynamic and stealth by use of stealth contour technology to constitute a new aerodynamic configuration layout.The method applied in aerodynamic design are as follows: A small aspect ratio and high sweepback blended wing body configuration with streak are used to improve the flow field in the root wing, and through the streak vortex stabilized the separated vortex in the nose of fuselage; To fix canard wing reasonably for making its vortex flow over wing in order to increase the vortex strength in upper wing then the vortex separation in the wing surface delays so as to get nonlinear lift of wing. Especially in high angle of attack the streak vortex in upper wing surface interfered with free vortex of canard wing and main vortex of wing formed nonlinear lift by synthesising of three vortices together,and greatly improved the flow characteristics for whole aircraft.The test proved that, this pilotless aircraft configuration has the advantage of high lift curve slope,high lift/drag ratio,high stalling angle and excellent longitudinal and lateral stability with comparison of the analogous ordinary configuration. The model measurement in an enechoic chamber proved that,the new project has also low RCS value in the front sector and in lateral sector.