燃烧加热类高超声速高温风洞流场校测与评估  

Calibration and Evaluation of Flow Field in Combustion-Heating Hypersonic High-Temperature Wind Tunnels

作　　者：伍军 李向东 蒲旭阳 毛雄兵 青龙 WU Jun;LI Xiang-dong;PU Xu-yang;MAO Xiong-bing;QING Long(Science and Technology on Scramjet Laboratory,Aerospace Technology Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心空天技术研究所高超声速冲压发动机技术重点实验室,四川绵阳621000

出　　处：《推进技术》2022年第10期363-369,共7页Journal of Propulsion Technology

摘　　要：为建立统一的燃烧加热类高超声速高温风洞流场品质评价标准,针对国内6座不同喷管出口直径的典型燃烧加热类高超声速高温风洞,从统一的皮托压探针、总温探针和流场校测排架设计出发,分别研制了流场校测装置,完成了典型试验状态的流场校测试验。根据相同的数据处理和分析方法得到了相关风洞喷管出口截面的速度场、温度场及均匀区信息。在马赫数4.5~6.0试验状态下,6座风洞速度场均匀区直径分别对应喷管出口直径的73.3%,76.5%,75.0%,80.0%,74.7%,83.3%。相应均匀区内马赫数标准偏差与平均马赫数的比值均小于2%,总温标准偏差与平均总温的比值均小于5%。各风洞的流场校测结果,体现了国内同类型风洞流场品质水平,可以作为当前燃烧加热类高超声速高温风洞流场品质评价的参考。To establish the uniform flow field quality evaluation criteria in the combustion-heating hypersonic high-temperature wind tunnels,the calibration tests were completed under typical conditions in six domestic same type wind tunnels. Corresponding to the different nozzle exit diameters,the calibration devices were manufactured respectively. Meanwhile,the pitot probes,the total temperature probes and the calibration rakes were designed by uniform methods. The information of velocity field,total temperature field and uniform region on the nozzle exit sections in those wind tunnels were obtained by the same calculation and analysis methods. The results indicate that under the test conditions of Mach numbers between 4.5 and 6.0,the uniform region diameter in each wind tunnel was separately 73.3%,76.5%,75.0%,80.0%,74.7%,83.3% relative to the nozzle exit diameter.Meanwhile,in each uniform region,the ratio of standard deviation and mean value of Mach number was less than2%,the ratio of standard deviation and mean value of total temperature was less than 5%. The calibration results reflect the level of flow field quality in the domestic same type wind tunnels and can be used for evaluation of the flow field quality in the current combustion heating hypersonic high-temperature wind tunnels for reference.

关 键 词：高超声速 高温 风洞 流场校测 均匀区 

分 类 号：V211.71[航空宇航科学与技术—航空宇航推进理论与工程]