高焓风洞一体化数值模拟及其对气动特性影响  

Integrated numerical simulation of high enthalpy tunnel and its effects on aerodynamic characteristics

作　　者：傅杨奥骁 董维中[1] 丁明松[1] 刘庆宗 江涛[1] FU Yang′aoxiao;DONG Weizhong;DING Mingsong;LIU Qingzong;JIANG Tao(Computational Aerodynamics Institute of 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计算空气动力研究所,绵阳621000

出　　处：《空气动力学学报》2020年第6期1075-1082,1101,I0002,共10页Acta Aerodynamica Sinica

摘　　要：基于高焓风洞喷管/试验段/试验模型一体化数值模拟的思路,通过数值求解三维热化学非平衡Navier-Stokes方程,开展了JF-10高焓激波风洞典型运行状态下流场的数值模拟,分析了喷管出口及试验段流场的非均匀性,研究了不同模型位置和攻角等试验条件下,不同数值模拟方法对试验模型气动力/热特性的影响规律。研究表明:1)由于喷管的扩张效应,喷管出口及试验段流场存在一定的非均匀性,在一些情况下,试验模型的流场特性可能会受到影响;2)与传统的将喷管和试验段模型流场解耦的数值模拟方法相比,采用一体化数值模拟考虑了喷管出口气体的扩张特性,可以提高高焓风洞流场数值模拟精度;3)解耦方法与一体化计算方法的差别大小受模型位置、攻角等多种因素影响,试验模型距喷管出口距离和模型攻角越大,解耦方法造成的误差越明显。基于一体化数值模拟的思想,数值计算可以更加深入地理解高焓风洞模拟特点,为风洞试验设计和试验测量数据对比分析奠定基础。In order to precisely predict test results in high enthalpy shock tunnel considering thermal-chemical non-equilibrium effects,based on the idea of integrated numerical simulation of nozzle/test section/test model flow filed,the simulation of JF-10 high enthalpy shock tunnel is conducted by solving three dimensional Navier-Stokes equations of non-equilibrium flow.The inhomogeneity of free stream in the test section has been analyzed,and the comparison of different simulation methods under various test conditions(i.e.distance from model to nozzle exit and attack angle)is presented.The results show that:1)the inhomogeneity of free stream in test section is obvious,and the characteristics of the test model flow filed can be influenced by it.2)compared to integrated numerical simulation,the traditional method shows discrepancies in the prediction of surface heat flux and aerodynamic coefficients for simulating nozzle and test model flow fields separately.3)the discrepancies are affected by the distance from model to nozzle exit and the attack angle of model,moreover,the discrepancies are increasingly significant when the distance and attack angle increase.4)the proposed integrated simulation method can truly reflect the test process in the tunnel and improve simulation accuracy,thus cooperate with tunnel test in cross comparison.

关 键 词：高焓激波风洞 热化学非平衡效应 一体化 数值模拟 气动力特性 气动热环境 

分 类 号：V211.22[航空宇航科学与技术—航空宇航推进理论与工程] V211.3