复合式高速直升机螺旋桨气动特性风洞试验研究  

Investigation on Propeller Aerodynamic Characteristics of Compound High-speed Helicopter

作　　者：徐栋霞 杨仕鹏 何龙[1,2,3] 彭先敏 章贵川[1,2] 黄志银 XU Dongxia;YANG Shipeng;HE Long;PENG Xianmin;ZHANG Guichuan;HUANG Zhiyin(Low Speed Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang 621000,China;State Key Laboratory of Aerodynamics,Mianyang 621000,China;School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,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,四川绵阳621000 [2]空天飞行空气动力科学与技术全国重点实验室,四川绵阳621000 [3]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《直升机技术》2024年第4期4-9,共6页Helicopter Technique

摘　　要：针对复合式高速直升机的特定飞行状态需求,对配套研制的推力螺旋桨开展气动特性风洞试验研究,获取了螺旋桨在直升机悬停状态、低速前飞状态、过渡前飞状态以及高速前飞状态的气动载荷、功率需求及效率。试验结果表明,随着前飞速度的增加,螺旋桨的拉力、扭矩及需用功率逐渐减小,螺旋桨效率逐渐增加,且在高速飞行时,螺旋桨效率基本不随飞行速度而变化。According to the typical flight state requirements of compound high-speed helicopter,the aerodynamic characteristics of the thrust propeller were studied by wind tunnel test and the aerodynamic load,power requirements and efficiency of the propeller were obtained in hover,low speed forward flight,transition flight,high speed forward flight.The results showed that with the increase of forward flight speed,the pull coefficient,torque coefficient and required power of the propeller decreased gradually,and in high speed flight status,the propeller efficiency was basically unchanged with the flight speed.

关 键 词：高速直升机 螺旋桨 气动性能 风洞试验 

分 类 号：V211.44[航空宇航科学与技术—航空宇航推进理论与工程]