电弧加热流场湍流度对尖锥边界层转捩影响的研究  

Sharp cone boundary layer transition research in arc heated flow field influenced by turbulence

作　　者：张骞[1] 陈连忠[1] 艾邦成[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《实验流体力学》2010年第6期57-60,共4页Journal of Experiments in Fluid Mechanics

摘　　要：电弧加热流场的热环境特性直接影响热防护系统的地面试验数据,由于电弧加热器高温气流和参数波动的原因,直接测量湍流度非常困难。为研究电弧加热流场湍流度对于边界层转捩的影响,采用红外热图热像仪,在电弧加热流场中进行了5°尖锥模型边界层转捩研究。结合数值计算,将试验结果与常规风洞的尖锥边界层转捩结果进行了比较。结果表明:马赫数影响的雷诺数转捩判别准则可以用于计算电弧加热流场的转捩雷诺数;电弧加热流场的尖锥边界层转捩雷诺数显著小于常规风洞的转捩雷诺数,表明在该试验条件下,电弧加热流场的湍流度显著大于常规风洞。Ground test data of heat shield system was directly influenced by heat environment characteristics in arc heated flow field,because of high temperature and parameters fluctuation in arc heater,it is very difficult to measure turbulence.In order to investigate boundary transition influenced by heat environment characteristics in arc heated flow field,sharp cone model aeroheating influenced by boundary layer transition had been studied in arc heated flow field using infrared thermo-graphical technology.Test models are 5° sharp cone steel and nonmental model,test results are analysed with numerical calculation method.Results are shown as followed： transition estimate by infrared thermo-graphical apparatus is feasible,sharp cone boundary layer transition Reynolds number is lower than conventional wind tunnel.It is shown turbulence in arc heated flow field is higher than conventional wind tunnel under this experiment condition.

关 键 词：湍流度 边界层转捩 电弧加热 雷诺数 尖锥 

分 类 号：V211.744[航空宇航科学与技术—航空宇航推进理论与工程]