某叶栅风洞栅前流场的分析与改进  

Analysis and improvement of flow field in front of a cascade wind tunnel

作　　者：王治敏[1] 徐让书[1] 赵长宇[1] 

机构地区：[1]沈阳航空航天大学航空航天工程学部(院),沈阳110136

出　　处：《沈阳航空航天大学学报》2016年第5期12-17,共6页Journal of Shenyang Aerospace University

摘　　要：为了探究造成叶栅风洞栅前测点处流动不稳定性的主要原因,以某平面叶栅风洞实验段为模型,使用数值模拟技术对叶栅实验器进行全场仿真,考察影响栅前测点处流动不均匀性的主要因素。结果表明,实验器上部角区产生的严重的流动分离会引起栅前测点来流产生大的偏转,通过加装叶片和测点下移的方法使得栅前测点处的流动得到很大改善。In view of a cascade wind tunnel＇s experimental section as a simulation model,the full flow filed was calculated using numerical simulation technology to explore the main reasons for causing unsteady flow at some test points which located in front of the cascades in a wind tunnel. The main factors that affected un- steady of flow at the test points were also investigated. The results show that serious flow separation in upper comer of the model causes the large deflection at the test points. Adding the blade and moving down the test points can greatly improve the flow at the test points.

关 键 词：叶栅风洞 流动不均匀性 数值计算 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]