FLOW SEPARATION IN SHOCK-WAVE BOUNDARY-LAYER INTERACTIONS

被引：3
|
作者：
HAMED, A [1 ]
KUMAR, A [1 ]
机构：
[1] NASA,LANGLEY RES CTR,THEORET FLOW PHYS BRANCH,HAMPTON,VA 23665
来源：
JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME | 1994年 / 116卷 / 01期
关键词：
D O I：
10.1115/1.2906816
中图分类号：
TH [机械、仪表工业];
学科分类号：
0802 ;
摘要：
This work presents an assessment of the experimental data on separated flow in shock wave turbulent boundary layer interactions at hypersonic and supersonic speeds. The data base consists of selected configurations where the only characteristic length in the iteration is the incoming boundary la,ver thickness. It consists of two-dimensional and axisymmetric interactions in compression corners or cylinder-flares, and externally generated oblique shock interactions with boundary layers over flat plates or cylindrical surfaces. The conditions leading to flow separation and the empirical correlations for incipient separation are reviewed. The effects of Mach number, Reynolds number, surface cooling, and the methods of detecting separation are discussed.
引用
收藏
页码：98 / 103
页数：6
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