实验流体力学Issue(6)：81-85,5.
激波风洞高超声速摩阻直接测量技术研究
摘要
Abstract
The research of direct measurement of skin friction in hypersonic shock tunnel is in-troduced in this paper.In the study,the piezoelectric skin friction balance was developed to test the skin friction of the model of engine inlet with compressed corner.In order to improve the pre-cision of calibration and experiment result,and easy to change between the calibration and wind tunnel experiment,a new skin friction balance structure was used.In this new structure,the skin friction balance has a separated measurement head with balance main body,which will en-sure the measurement head and calibration head could be changed in different situations.The measurements were conducted in the flow field with the nominal mach number of 8 and 10,Reyn-olds number of 2.85×10 7/m and 1.58×10 7/m in0.6m shock tunnel of CARDC.The heat flux near the skin friction test location was tested using platinum thin film sensors,the results are co-incided with the Reynolds analogy.关键词
激波风洞/高超声速飞行器/摩擦阻力/天平校准/天平设计Key words
shock tunnel/hypersonic aircraft/skin friction/balance calibration/balance design分类
航空航天引用本文复制引用
吕治国,李国君,赵荣娟,姜华,刘济春,王刚..激波风洞高超声速摩阻直接测量技术研究[J].实验流体力学,2013,(6):81-85,5.基金项目
装备预研基金 （）
