喷管尺寸对电弧风洞流场和热环境的影响分析  

Influence Analysis of Nozzle Size on Flowfield and Thermal Environment in Arc-heated Wind Tunnel

作　　者：罗万清 梁剑寒[1] 杨远剑[2,3] 赵金山[2] 孙海浩 LUO Wan-qing;LIANG Jian-han;YANG Yuan-jian;ZHAO Jin-shan;SUN Hai-hao(Science and Technology on Scramjet Laboratory,National University of Defense Technology,Changsha 410073,China;Hypervelocity Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;School of Astronautics,Harbin Institute of Technology,Harbin 150080,China)

机构地区：[1]国防科技大学高超声速冲压发动机技术重点实验室,长沙410073 [2]中国空气动力研究与发展中心超高速空气动力研究所,绵阳621000 [3]哈尔滨工业大学航天学院,哈尔滨150080

出　　处：《宇航学报》2021年第2期159-166,共8页Journal of Astronautics

基　　金：国家自然科学基金(91641201)。

摘　　要：为获得电弧风洞喷管尺寸对试验流场以及模型表面热流的影响规律,针对某特定模拟参数试验状态,采用高焓流动数值模拟方法对不同尺寸锥形喷管下的球柱校核模型试验流场进行了模拟和比较分析。研究发现,在模拟气流焓值和模型驻点热流的条件下,采用出口尺寸小的喷管所需电弧加热功率更低,同时单位流向截面上气流能量转化为模型驻点气动热的比例更低。不同喷管出口尺寸下,试验流场喷管出口区域热力学非平衡程度、波后氧原子质量分数、模型驻点区域压力以及表面传导热流和扩散热流占比都比较接近,但相较飞行状态存在明显差异;不同喷管出口尺寸下来流速度、激波脱体距离以及驻点线上平动温度之间的差异明显,喷管出口尺寸越大,其与飞行状态越接近。In order to obtain the influence of nozzle size on the test flowfield and the heat flux on the model surface in an arc-heated wind tunnel,the numerical simulation method is used to simulate and analyze the high enthalpy flowfield of the spherical cylinder calibration model with different sizes of conical nozzles for specific test parameters.The comparison of the flowfield characteristics and the heat flux on the model surface reveals that,under the condition of simulating enthalpy and stagnation point heat flux,the nozzle with small exit size requires lower arc heating power,and the ratio of airflow energy transferred to aerodynamic heat per unit section is lower.At different nozzle exit sizes,the thermodynamic nonequilibrium degree in the exit region,the mass fraction of oxygen atom after shock wave,the pressure in the region near the stagnation point,and the proportion of conduction heat flux and diffusion heat flux are all approximate,while with any sizes of nozzles their differences between the ground experiment and the flight are obvious.The difference between the inflow velocity,the stand-off distance of shock wave and the translational temperature on the stagnation line are obvious.The larger the nozzle exit size is,the more similar they are to the flight condition.

关 键 词：喷管尺寸 电弧风洞 高焓流场 数值模拟 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]