摘要
有压缩拐角区域的突起物的局部气动加热问题表现为流动的分离与再附。许多研究人员对这类突起物的气动加热问题做了大量的理论和实验研究。本文通过对其流动情况的分析，结合大量的实验数据，对压缩拐角区域气动加热问题，给出了一种有效的工程计算方法。
The local aerodynamic heating of the protuberance which has a compression corner region,is characterized by flow separation and reattachment Many researchers conducted theoretical and experimental works on the aerodynamic heating of this kind of protuberance This paper through the analysis of the flow combined with many experimental data gives an engineering method of estimation of aerodynamic heating around the compressin corner
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1998年第1期98-102,共5页
Journal of Astronautics
关键词
气动加热
突起物
分离
再附
飞行器
Aerodynamic heating Protuberance Compression corner Separation Reattachment
