摘要
报道了在JF-10氢氧爆轰驱动高焓激波风洞中开展的再入流场红外辐射实验研究．风洞的试验状态为: 驻室总压19．6 MPa,总焓15．5 MJ／kg,自由流速度约5 km／s．实验以锑化铟多元红外成像系统为测量手段,以球头钝锥体为试验模型,测量激波层与近尾流中红外辐射功率的横向分布剖面．试验数据呈现明显的规律性．试验结果表明,激波层内壁面附近的红外辐射功率较小,中间有一区域辐射较大且相对均匀,激波层外缘辐射单调减小;尾流中红外辐射功率在轴线附近的核心区最大,随着离轴线距离的增大而单调减小．
This puper reports our experimental research on infrared radiation in reentry flows. The experiments are conducted in the oxygen-hydrogen detonation driven shock tunnel JF-10. Total enthalpy of the particular run amounts to 15.5 MJ/kg, pressure in the reservoir is 19.6 MPa, and the generated free stream velocity is approximately 5 km/s. InSb multi-element infrared imaging system is used to measure the infrared radiation. Taking a sphere-nosed blunt cone as the test model, the transverse infrared radiation power profiles in the shock layer and wake are obtained. The data show some unique features. Infrared radiation is weak near the wall, strong and relatively uniform in the middle region of the shock layer, and becomes weak again in the outer part of the shock layer. In the wake, the radiation is the strongest near the symmetric axis and becomes weaker monotonically while departing from the axis.
出处
《力学学报》
EI
CSCD
北大核心
2006年第4期446-451,共6页
Chinese Journal of Theoretical and Applied Mechanics
基金
国家自然科学基金资助项目(10472125).~~
关键词
高焓激波风洞
风洞实验
再入流场
红外辐射
测量技术
measurement high enthalpy shock tunnel, wind tunnel experiment, reentry flow field, infrared radiation, technique
