摘要
给出三维和二维压缩拐角诱导激波与高超声速层流和湍流边界层相互作用的流场结构和前向压缩表面的热流率分布。实验气流M数为7．8，单位长度Re数为3．5×107／m。结果表明：激波与边界层相互作用能促进边界层转捩。只有基于再附峰值热流率位置长度的参考温度条件下的雷诺数足够低，相互作用过程才能是纯层流的。在全再附高超声速分离流中，再附峰值热流率可用Simeonides通用相关式进行估算。
This paper presents flowfield structures and heat transfer distributions on compression ramp in the interaction between shock/hypersonic laminar and turbulent boundary layer induced by three-and two-dimensional compression comer. The nominaltest conditions were freestream Mach number of 7. 8 and unit Reynolds number of 3. 5 ×10 7/m. The laminar-turbulent transition is promoted by the interaction process. The process doesn't exhibit fully laminar unless the reference Reynolds number based on the location of peak heat transfer on compression ramp is low enough. In hypersonic separated flow with fully reattachment,the peak heat transfer of reattachment may be predicted by the agency of Simeonides' universal correlation.
出处
《流体力学实验与测量》
CSCD
1997年第3期23-27,共5页
Experiments and Measurements in Fluid Mechanics
基金
国家高技术研究发展计划航天技术领域资助
关键词
高超音速流动
激波
边界层
再附峰值热流率
hypersonic flow
separated flow
shock/boundary layer interaction
peak heat transfer of reattachment
compression corner
