CARDC的直升机气动力试验研究新进展  

Recent Progresses of Helicopter Aerodynamic Test and Research at CARDC

作　　者：杨永东[1] 袁红刚[1] 黄明其[1] 杨炯[1] 

机构地区：[1]中国空气动力研究与发展中心,绵阳621000

出　　处：《直升机技术》2008年第3期129-134,共6页Helicopter Technique

摘　　要：中国空气动力研究与发展中心(CARDC)自1990年建成12m×16m/8m×6m低速风洞直升机旋翼模型试验台以来,在8m×6m风洞进行了多种直升机旋翼模型试验;2001年,首次在12m×16m试验段进行了旋翼及旋翼/机身组合模型试验,为新型直升机的研制做出了贡献。2003年以来,通过开展某工程配套技术改造项目,建成了2m旋翼模型试验台、尾桨及旋翼/机身组合模型试验台;配套研制了高性能的数据采集和监视报警系统;配备了频闪仪、动态信号记录仪等专用设备,大大提高了CARDC的直升机气动力试验能力。"十五"期间,还开展了直升机试验技术和试验数据精准度研究、直升机试验数据相关性研究,掌握了先进的旋翼前飞配平试验技术、悬停地面效应试验技术,初步建立了旋翼模型风洞试验数据的洞壁干扰修正方法、悬停试验数据的Re数影响修正方法,进一步提高了CARDC的直升机风洞试验技术水平。目前,CARDC具备了系统研究直升机模型气动力的试验能力,可以为新型直升机的研究和发展提供技术支持。Since the CARDC helicopter rotor model test stand for 12m×16m/8m×6m low speed wind tunnel was established in 1990,many sorts of helicopter rotor model tests have been conducted in the 8m×6m test section.The rotor and fuselage combined model tests of a new type helicopter were conducted in the 12m 16m test section for a first time.Recently,the 2m diameter rotor model test stand and the tail and main rotor and fuselage combined model test rig were established,and the data acquire and monitor system was developed.The helicopter model test ability of CARDC has been grown greatly by the development of those stand and device.Since 2001,by the research of rotor test technique and test result correlation,the techniques of trimmed forward flight test and hover ground effect test were developed,the elementary test result correction methods of wind tunnel wall effect and Re number effect were established.Presently,CARDC is capable of carrying out helicopter aerodynamic tests and the relative research projects for the development of new type helicopter.

关 键 词：直升机 空气动力 气动试验 低速风洞 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]