低雷诺数平面叶栅试验方法研究  

Experimental Investigation Methods on Low Reynolds Number Plane Cascade

作　　者：凌代军[1] 姜正礼[1] 于进涛[1] 马昌友[1] 

机构地区：[1]中国燃气涡轮研究院,四川江油621703

出　　处：《燃气涡轮试验与研究》2011年第3期1-6,共6页Gas Turbine Experiment and Research

摘　　要：传统的叶型气动设计体系建立在高雷诺数基础上,UAV(无人飞行器)的发展对低雷诺数叶型气动设计和试验验证提出了新的要求。本文就降低叶型试验雷诺数的原理、实现的方法进行了分析,提出了在现有试验器基础上进行设备改造的方案和试验调节方法,并根据试验数据对改造后试验器的低雷诺数流场进行了初步分析,在国内首次通过试验手段获得了某高亚声速扩压叶型气动性能参数在低雷诺数条件下的特性。The conventional airfoil design system is based on high Reynolds number, but the development of UAV （unmanned aerial vehicle） has offered the new demands on airfoil design and experimental verifi- cation under low Reynolds number condition. This paper analyses the theory and methods for low Reynolds number cascade aerodynamic performance. The reconstructive project and experiment adjusting methods of facility are given, and low Reynolds number flow field after the reconstruction based on test data is analyzed. In China, it is the first time that aerodynamic performance parameters change under low Reynolds number of a high subsonic speed diffused airfoil are got by means of test.

关 键 词：低雷诺数 平面叶栅 气动性能 试验研究 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]