大飞机缝翼滑轨影响研究  

Research on influence of slat brackets of large airplane

作　　者：许可[1] 章荣平[1] 张刘[1] 郝南松[1] 

机构地区：[1]中国空气动力研究与发展中心低速空气动力研究所,四川绵阳621000

出　　处：《空气动力学学报》2016年第3期368-372,共5页Acta Aerodynamica Sinica

摘　　要：通过数值模拟和风洞实验两种手段研究了大飞机缝翼滑轨对飞机气动性能的影响。分析了缝翼滑轨对缝道和机翼表面流动分布的影响,获得了缝翼滑轨参数对飞机气动性能的影响规律。数值模拟结果表明:缝翼滑轨对缝道内的流动形成了阻塞,改变了机翼表面的流动形态,减小了机翼附面层流动速度,降低了飞机的失速性能。实验结果表明:通过减小滑轨宽度、减少滑轨数量、采用圆形截面滑轨和滑轨外弯等能够有效降低滑轨影响,改善飞机失速性能;滑轨参数对小尺度模型实验结果的影响尤为显著。研究结果为3m量级和8m量级风洞缝翼滑轨模型设计提供了参考。Influence of slat brackets on aerodynamic performance of a large airplane was obtained through numerical simulation and wind tunnel test. Slat brackets？ influence on flow around slat gap and wing surface was analysed, a n d the rules of influence of the parameters of slat brackets were obtained. Results of numerical simulation show that flow around wing surface is changed,flow velocity around boundary layer decreases and brings some degradation of stallperformance as a result of blocking due to slat brackets. Results of wind tunnel test show thatstall performance can be improved by the ways of reducing width and quantity of slat brackets as well as using slat brackets with circular cross section and outward bending？ and the test results of small scale models are significantly influenced by the parameters of slat brackets. Study results can provide designing reference for slat brackets model in both 3 m and 8 m magnitude windtunnel.

关 键 词：大飞机 缝翼滑轨 数值模拟 风洞实验 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] V211.7