Abstract: In order to better carry out thermal assessment test of protection materials or structures of hypersonic aircraft in the arc-heated wind tunnel, based on the finite volume discretization, a numerical simulation method for solving the multi-component thermochemical non-equilibrium flowfield was established for the high enthalpy test state. The high enthalpy flowfield was simulated for different test models in the 20MW arc-heated wind tunnel at the China Aerodynamics Research and Development Center (CARDC), and the flowfield characteristics and the heat flux on the model surface were obtained. The calculation method was verified by comparison with the experimental datas. It is found that in the case where axial distance between the nozzle outlet and the test model is very close, the nozzle flowfield and the model flow can be separately simulated. The obtained heat flux on the model surface is very close by using the Gupta’s 7 species and 5 species air chemical reaction data, and the results using double temperature model are closer to the experimental measurement results than the single temperature model. The surface heat flux of the test model obtained by calculation and experimental measurement under multiple state conditions was compared, and the difference between the two is within 15%. The reliability of the numerical method for simulating the flowfield of this wind tunnel was verified.

Key words: Arc-heated wind tunnel;Thermal assessment test;High enthalpy state;Numerical simulation;Thermochemical non-equilibrium

摘要： 为了在电弧风洞更好地开展高超声速飞行器防热材料或结构热考核试验，基于有限体积离散，建立了针对电弧风洞高焓试验状态的多组分热化学非平衡流场数值模拟方法。针对中国空气动力研究与发展中心20MW电弧风洞不同试验模型的高焓流场进行了模拟，获得了试验状态的流场特性和模型表面热流分布，通过与试验测量值比较验证了计算方法。研究发现在喷管出口和试验模型之间的轴向距离很近的情况下，可以采用喷管流场和模型绕流分开模拟。通过对比数值模拟方法中的热化学模型，表明采用Gupta 7组分和5组分空气化学反应数据获得的模型表面热流非常接近，同时相比单温度模型结果，双温度模型结果与试验测量结果更接近。比较了多个状态条件下计算和试验测量获得的试验模型表面热流，发现二者相差都在15%以内，验证了建立的数值方法模拟该风洞高焓流场的可靠性。

关键词: 电弧风洞;热考核试验;高焓状态;数值模拟;热化学非平衡