摘要
为了研究高超声速进气道内激波干扰和流场结构，对一个二维进气道模型在中国空气动力研究与发展中心超高速所风洞流场中进行了实验（Ｍ＿∞＝５．０，Ｒｅ＿∞＝７．５×１０￣６ｍ￣（－１））。采用纹影方法，结合压力测量对进气道内流结构进行诊断，同时用Ｙｅｅ的ＴＶＤ有限差分格式通过求解二维Ｎ─Ｓ方程对相应实验状态下的进气道内流场进行了数值模拟。风洞实验与数值模拟取得了较好的一致。进一步的分析还表明高超声速进气道内的激波─边界层干扰对进气道性能有很大的影响。
In order to investigate the shock interactions and flow struc-ture in high speed inlets. A 2-D inlet model was tested in CARDC's fa-cility at free stream Mach number of 5.0. Wall static pressure were measured, pitot pressure were measured near the inlet exit and schlieren photographs were taken. The inlet internal flow structure was well visu-alized by the schlieren photographs and pressure data. The test results were compared to numerical predictions obtained from a 2-D N-S codedeveloped by author. A primary analysis for the flow structure about the inlet model was presented in terms of the experimental and computa-tional results.
出处
《空气动力学学报》
CSCD
北大核心
1995年第1期28-33,共6页
Acta Aerodynamica Sinica
关键词
高超声速
进气道
激波
边界层
风洞实验
high speed inlet, flow structure, shock-boundary layer interactions, wind tunnel test,numerical simulation.
