CHN-T1标模2.4米风洞气动特性试验研究  

Experimental study of aerodynamic characterictics of CHN-T1 standard model in 2.4 m transonic wind tunnel

作　　者：李强[1,2] 刘大伟[1,2] 许新[1,2] 陈德华[1] LI Qiang;LIU Dawei;XU Xin;CHEN Dehua(State Key Laboratory of Aerodynamics,Mianyang 621000,China;High Speed Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]空气动力学国家重点实验室,绵阳621000 [2]中国空气动力研究与发展中心高速空气动力研究所,绵阳621000

出　　处：《空气动力学学报》2019年第2期337-344,共8页Acta Aerodynamica Sinica

基　　金：国家重点研发计划(2016YFB0200700)

摘　　要：大飞机标模可用来校验风洞流场品质,检验和提高大型飞机风洞试验数据质量,标模的外形特点及其气动特性能否反应现代大飞机设计特点尤为重要。气动中心前期已完成了一套大展弦比飞机标模CHN-T1的设计研制,为了验证设计结果,在2.4米跨声速风洞中进行了一期验证试验,试验Ma数范围0.40～0.90,模型名义迎角-6°～15°,侧滑角-3°～12°,雷诺数Re=(3.3～7.5)×10~6。试验内容包括纵横航向基本特性试验、重复性精度试验、变雷诺数试验、转捩对比试验、流谱观察试验和变形测量试验。结果表明,该飞机外形具有良好的升阻特性,符合现代大展弦比飞机的典型气动特征,可用于2.4m跨声速风洞大型飞机标模试验数据体系建设。Large aircraft standard model can used in validating the flow field quality of transonic wind tunnels,checking and improving the experimental data quality.It is important that the outline characteristics and aerodynamic performance of standard model reflect the design of modern large aircraft.A new high-aspect-ratio aircraft model was designed by CARDC,and a validation test was conducted in 2.4 m transonic wind tunnel with test Mach number from 0.40 to 0.9,with the angle of attack ranges from-6° to 15°,side slip angle from-3° to 12°,and Reynolds number from 3.3×10 6 to 7.5×10 6.The test contents consist of basic characteristic test,repeatability test,Reynolds number variation test,transition method comparison test,surface oil flow visualization test,and model deformation test.The results indicate that,the model designed shows good lift-to-drag characteristics,meeting the typical aerodynamic characteristics of modern high-aspect-ratio aircraft,and can be used in the construction of large aircraft data system in 2.4m transonic wind tunnel.

关 键 词：大展弦比 标模 风洞试验 高速风洞 气动特性 

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]