CAJ | 학술논문

小展弦比飞翼标模为国内自主设计的融合体飞翼通用研究模型，前缘后掠角为65°，展弦比为1．54。风洞试验结果表明小展弦比飞翼标模在跨声速迎角4°开始出现非线性升力，在迎角12°至16°范围内会出现升力突然下降、俯仰力矩突然上扬的现象。为了分析该现象的机理，通过数值模拟的方法研究了小展弦比飞翼标模在马赫0．9时的流动特性，分析了前缘涡的产生、发展直至破裂的整个过程，结果表明：小展弦比飞翼标模在迎角4°开始出现涡升力；随着迎角增加，前缘涡逐渐向内侧移动，涡强和背风面激波的强度也逐渐增加，前缘涡与激波发生交叉干扰并达到一个平衡流态；当前缘涡与激波无法维持既有平衡时则会发生涡破裂，流场急剧变化以达到新的平衡，从而导致升力突然下降并产生抬头力矩增量。
소전현비비익표모위국내자주설계적융합체비익통용연구모형，전연후략각위65°，전현비위1．54。풍동시험결과표명소전현비비익표모재과성속영각4°개시출현비선성승력，재영각12°지16°범위내회출현승력돌연하강、부앙력구돌연상양적현상。위료분석해현상적궤리，통과수치모의적방법연구료소전현비비익표모재마혁0．9시적류동특성，분석료전연와적산생、발전직지파렬적정개과정，결과표명：소전현비비익표모재영각4°개시출현와승력；수착영각증가，전연와축점향내측이동，와강화배풍면격파적강도야축점증가，전연와여격파발생교차간우병체도일개평형류태；당전연와여격파무법유지기유평형시칙회발생와파렬，류장급극변화이체도신적평형，종이도치승력돌연하강병산생태두력구증량。
The low-aspect-ratio flying-wing configuration was designed as a common research model in China,wind tunnel test results show lift force experience a sudden decrease at M=0.9 as the angle of attack between 12°and 16°,numerical methods are also used to investigate this be-havior in detail.The generation,development,and breakdown of vortex are all concerned.Re-sults show that the flying-wing generates vortex lift atα=4°,Shock/vortex interaction is respon-sible at transonic speed,as the angle of attack increases.As long as the shock is strong enough to break the balance between shock and vortex,vortex breakdown would occur and new balance mechanism would set up.