CAJ | 학술논문

采用经风洞试验验证的CFD计算方法和网格生成策略，以某型大型民用运输机基本三段增升装置着陆构型为对象，研究短舱涡流片及其参数对增升装置效率的影响。研究表明：短舱涡流片的流动机理与大后掠三角翼类似，其所诱导漩涡流动的强度、上下位置以及展向位置是影响增升效率的3个关键因素。空间涡下移、向机翼外侧移动或增加其强度均可以提高增升装置的效率。其中涡流片下偏会使空间涡下移且向机翼内侧移动，但是对机翼上方空间涡强度的影响并不是单调的；涡流片后移可以增强机翼上方空间涡强度并使其下移，但是也会造成空间涡向机翼内侧移动；增加涡流片的安装角或者倾角可以增强机翼上方空间涡强度并使其向机翼外侧移动，但是会造成空间涡上移；增加涡流片的后掠角（即减小其前缘附近的面积）使空间涡下移并向机翼外侧移动，但是会造成空间涡强度减弱。所以这些参数（上下位置、前后位置、安装角等）对全机升力系数的影响都不是单调的，需要大量的流场分析方能找到较优的参数组合。同时短舱涡流片还会受到巡航状态、发动机反推和结构等方面的约束，设计过程中需要综合考虑各种影响因素。
채용경풍동시험험증적CFD계산방법화망격생성책략，이모형대형민용운수궤기본삼단증승장치착륙구형위대상，연구단창와류편급기삼수대증승장치효솔적영향。연구표명：단창와류편적류동궤리여대후략삼각익유사，기소유도선와류동적강도、상하위치이급전향위치시영향증승효솔적3개관건인소。공간와하이、향궤익외측이동혹증가기강도균가이제고증승장치적효솔。기중와류편하편회사공간와하이차향궤익내측이동，단시대궤익상방공간와강도적영향병불시단조적；와류편후이가이증강궤익상방공간와강도병사기하이，단시야회조성공간와향궤익내측이동；증가와류편적안장각혹자경각가이증강궤익상방공간와강도병사기향궤익외측이동，단시회조성공간와상이；증가와류편적후략각（즉감소기전연부근적면적）사공간와하이병향궤익외측이동，단시회조성공간와강도감약。소이저사삼수（상하위치、전후위치、안장각등）대전궤승력계수적영향도불시단조적，수요대량적류장분석방능조도교우적삼수조합。동시단창와류편환회수도순항상태、발동궤반추화결구등방면적약속，설계과정중수요종합고필각충영향인소。
Carefully considering the landing configuration of a large civil transport aircraft , we apply the CFD com-putational method and mesh generation strategy , whose validity is confirmed by wind tunnel experiments conducted by us, to study the influence of nacelle chine on high-lift efficiency.The results show that the flow mechanism of nacelle chine is similar to that of large sweep delta wing .The intensity and the location of vortex flow , which are induced by nacelle chine , are the key elements of high-lift efficiency .Moving the vortex outer or downward or en-hancing its intensity can increase high-lift efficiency .Through putting nacelle chine downward , the vortex will be moved downward and outboard of wing , but the influence of intensity will not show a monotonic way .The vortex will move upward and inboard of wing and its intensity will be enhanced by putting nacelle chine backward .In-creasing the angle incidence or obliquity of nacelle chine can move the vortex upward and outboard of wing , and both of them can increase the intensity of vortex .Increasing the sweep angle ( reducing the area near leading edge ) of nacelle chine will move the vortex downward and outboard of wing , but its intensity will be reduced .Therefore, the influence of these parameters ( location , angle of incidence and so on ) upon high-lift efficiency are not mono-tonic .Getting the optimum parameter combination needs a lot of analysis of flow fields .Besides , the design of na-celle chine will be restricted by cruise configuration , the reverse thrust device and the structure of engines; they must be taken into consideration in design process .