共轴刚性旋翼高速直升机风洞试验研究综述  

Overview of Wind Tunnel Test for Coaxial Rigid Rotor

作　　者：黄明其[1] 王亮权 何龙[1] 王畅[1] 唐敏[1] HUANG Mingqi;WANG Liangquan;HE Long;WANG Chang;TANG Min(China Aerodynamics Research and Development Center,Low Speed Aerodynamics Institute,Mianyang 621000,China)

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,绵阳621000

出　　处：《南京航空航天大学学报》2021年第2期216-225,共10页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：共轴刚性旋翼高速直升机是下一代直升机发展的重点构型之一,风洞试验是突破其中关键空气动力学技术、推动该构型直升机从原理验证走向型号研制所依赖的重要手段。文中对国内外共轴刚性旋翼试验设施及相关风洞试验进行了介绍,综述了共轴刚性旋翼升力偏置、流场显示与测量、桨毂减阻、推进螺旋桨和机身气动特性等技术领域的试验研究概况及主要成果。结合国内外研究现状,对中国共轴刚性旋翼高速直升机在风洞试验设备建设、研究能力拓展以及试验结果应用等方向的发展提出了思考。High speed helicopter with coaxial rigid rotor is one of the most promising configurations for the next generation helicopter.Wind tunnel experiment is an important way in helicopter aerodynamics research and in the development of a new helicopter.The current status of wind tunnel tests on coaxial rigid rotor is examined in this paper.A brief history of the developed test facilities is given.The review is followed by the research results on different aerodynamic problems,e.g.,lift offset,flow field visualization and measurement,drag reduction of hub,propeller and fuselage test.Considering the characteristics of previous studies,the prospects of wind tunnel experiment for coaxial rigid rotor on test rig development,research capability improvement,and test results application are presented.

关 键 词：共轴刚性旋翼 高速直升机 风洞试验 升力偏置 桨毂减阻 螺旋桨 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]