基于侧壁边界层控制的翼型二维流动准则研究  

The Investigation of Two-dimensional Flowing Rule on Airfoil Based on Sidewall Boundary Layer Control

作　　者：惠增宏[1] 张传侠[1] 

机构地区：[1]西北工业大学翼型、叶栅空气动力学国家级重点实验室,西安710072

出　　处：《弹箭与制导学报》2012年第5期133-136,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家高技术研究发展计划(2007AA05Z448)资助

摘　　要：采用翼型中剖面与端面剖面对应点压力值对比的数据处理方法,在NF-3风洞对WA-A210翼型表面流动进行了侧壁边界层吹气控制实验研究,探索模型在失速迎角附近的最佳吹气动量系数与二维流动之间的匹配规律,得到了翼型模型不同状态下的最佳吹气动量系数的判断准则。结果表明:1)利用这一数据处理方法得到的准则能够判断翼型表面的二维流动状态;2)采用侧壁吹气方案改善了翼型表面二维流动,减小了侧壁边界层对翼型实验结果的影响。In order to obtain the matching criterion on optimal blowing momentum coefficient near the stall angle of attack for the tested airfoil model,the WA-A210 airfoil with sidewall boundary layer blowing control was tested in NF-3 wind tunnel.A special data processing method was used by subtracting the acquired pressure data in the same station between middle section profile and side section profile on airfoil surface,and the best blowing momentum coefficient can be obtained in different state on airfoil model.The results show that it can judge two-dimensional flowing state on the surface of airfoil by using the rule from this data processing method,sidewall blowing control can improve two-dimensional flowing on the surface of airfoil and decrease the effect of sidewall boundary layer on the airfoil experiment result.

关 键 词：翼型 风洞 侧壁边界层 吹气控制 吹气动量系数 

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]