CAJ | 학술논문

在中等展弦比直机翼上设计了由前缘到翼梢端面的四个环形通气孔。采用点对接网格和面搭接网格技术，基于雷诺平均N-S方法，分别选用S-A湍流模型和SST湍流模型，研究了翼尖开孔吹气对机翼尾涡的影响。计算结果表明，翼尖开孔吹气能够显著地耗散翼尖尾涡。从孔中吹出的气流对来流有明显的阻挡作用，能够相应地减小尾涡内的轴向速度，同时孔的出口附近会产生一对方向相反的涡，能够削弱尾涡区内的旋转效应。与其他翼尖展向吹气流动控制措施相比，翼尖开孔吹气方式具有不需要引气来源，结构简单，易于工程实现等优点，是一种良好的尾涡耗散技术。
재중등전현비직궤익상설계료유전연도익소단면적사개배형통기공。채용점대접망격화면탑접망격기술，기우뢰낙평균N-S방법，분별선용S-A단류모형화SST단류모형，연구료익첨개공취기대궤익미와적영향。계산결과표명，익첨개공취기능구현저지모산익첨미와。종공중취출적기류대래류유명현적조당작용，능구상응지감소미와내적축향속도，동시공적출구부근회산생일대방향상반적와，능구삭약미와구내적선전효응。여기타익첨전향취기류동공제조시상비，익첨개공취기방식구유불수요인기래원，결구간단，역우공정실현등우점，시일충량호적미와모산기술。
Four annular slots from leading edge to the tip surface are designed on a fixed wing with middle aspect ratio .Combined with the point-to-point and patched structured grid techniques , RANS methods with S-A and SST turbulence models are employed to investigate the slotted tip effects on wake vortex . Results show that vortex in the rear wake can be significantly dissipated by slotted tip .Air blowing out from the slots can block the flow and reduces the axial velocity in the wake .Counter-rotating vortex pair can be formed at downward of each slot exit ,and the rotational effects can be weakened .Compared with other spanwise blowing techniques ,the slotted tip in this research features simple structure and easy ap-plication to engineering with no additional air sources ,and thus should be a promising vortex dissipation technique .