中北大学学报（自然科学版）2017，Vol.38Issue(5)：609-613,5.DOI:10.3969/j.issn.1673-3193.2017.05.018
高超声速绕平板直立舵干扰气动热研究
Investigation on Aerodynamic Heating Characteristics of Hypersonic Flat Pate/Cylinder Juncture Flow
摘要
Abstract
In order to study the aerodynamic heating problems induced by shock wave/boundary layer in-teractions,experiments were conducted in JF12 shock tunnel in Institute of Mechanics,Chinese Acade-my of Sciences,which is capable of duplicating the hypersonic flight conditions.A flat plate with rela-tively large size and removable cylinder were selected and coaxial thermal couples were used to measure the heat transfer.Corresponding numerical simulations were also conducted in effort to better under-stand the phenomena accompanying in these experiments.Results show that double-peak structure of the heat flux distribution in front of the cylinder exist,due to the separation and reattachment phenome-non in the interference area.The peak heat flux,19 times of which without interaction,was obtained lo-cated 0.2 times of the cylinder diameter ahead.Besides,the interaction region was developed backward as a shape of horseshoe vortex.关键词
高超声速/激波/边界层干扰/气动热/激波风洞Key words
hypersonic flow/shock wave/boundary layer interaction/aerodynamic heating/shock tunnel分类
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栗继伟,汪球,赵伟..高超声速绕平板直立舵干扰气动热研究[J].中北大学学报（自然科学版）,2017,38(5):609-613,5.基金项目
国家自然科学基金资助项目(11402275) （11402275）
山西省重点研发计划项目(201603D121012) （201603D121012）
