低速大迎角尾撑支架干扰试验研究  

Investigation on the interference of rear sting supports at high angle of attack in low speed wind-tunnel

作　　者：王勋年[1] 祝明红[2] 孙传宝[2] 

机构地区：[1]西北工业大学,西安710072 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2007年第2期8-12,共5页Journal of Experiments in Fluid Mechanics

摘　　要：飞行器低速大迎角风洞试验是飞行器研制中必须进行的试验研究项目,而进行大迎角试验时飞行器模型大多采用尾部支撑方式支撑,目前国内对低速大迎角风洞试验结果中的支架干扰都没有进行相应的扣除。本项研究成果可作为今后支架干扰研究或扣除的参考,重点介绍了在中国空气动力研究与发展中心3.2m风洞中,利用张线支撑系统进行有预弯接头的尾撑支架干扰试验研究,获得了预弯尾撑支架干扰随迎角、侧滑角的变化规律,分析了不同形状尾撑支杆的支架干扰特性;并对尾撑支杆的几何参数进行了研究,获得了尾撑支杆长度对尾撑支架干扰量的影响规律,提出了尾撑支杆设计的建议。The high alpha aerodynamic of low speed wind tunnel experiments are necessary for the future advanced aircrafts, and the most of aircrafts models are supported by rear sting, but the interference of sting are not deducted from the test results before, in order to research the interference of the sting, this study was conducted in CARDC and the results can be referenced to the other aircrafts models for low speed wind tunnel test. The investigation of interference on the rear sting supports system was carried out in the Ф3.2m wind tunnel of CARDC, the airplane model was supported with the extension system and the rear rigs was fixed on the end of balance, then, the interference of rear rig could be gotten. The quantity of the interference of the rear rigs and its rules varying with the a and the β are presented in this paper, at the same time, the influence of various configuration of rear rigs on the interference rules have been analyzed. Some sugguestions for the rear rig design are brought forward in the paper too.

关 键 词：尾撑 支架干扰 大迎角 试验研究 低速风洞 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程] V211.7