直升机旋翼模型风洞试验述评  

REVIEW ON HELICOPTER ROTOR MODEL WIND TUNNEL TEST

作　　者：王懋勋[1] 庄开莲[1] 

机构地区：[1]中国空气动力研究与发展中心

出　　处：《气动实验与测量控制》1991年第3期9-17,共9页

摘　　要：为研制新型直升机,必须重视对直升机空气动力学的研究。本文简述了直升机旋翼模型风洞实验的重要性及与固定翼模型风洞实验的区别。根据直升机旋翼空气动力学的特点说明了开展旋翼风洞实验对风洞、模型及实验设备的特殊要求、着重说明直升机旋翼实验台是进行旋翼风洞实验必须的基础设备。同时对国外直升机旋翼模型风洞实验技术的发展状况作了简要介绍。最后回顾了我国直升机旋翼模型风洞实验技术研究方面取得的一些进展及与国外的差距。并对型号研制必须进行的一些风洞实验内容作了介绍。For the development of new type helicopters effortsmust be made on the research of helicopter aerodynamics.The im-portance of helicopter rotor model experiments in wind tunnel and thedifferences from those fixed wing model tests are briefly discribed inthis paper.Special requirements to the wind tunnel,model and testequipments for rotor tests,due to features of helicopter aerodynamics,are explained,with emphasis on that the helicopter rotor test stand isa necessary basic facility.The paper also gives a brief inctroductionto the development of helicopter rotor test techniques abroad,finally,progresses of helicopter rotor test techniques made in our country andcomparison with those in other countries are reviewed.

关 键 词：直升机 风洞试验 旋翼 空气动力学 

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]