LENS风洞试验返回器模型气动热特性模拟

国家数值风洞高超声速流动模拟软件HyFLOW的研制对打破国外同类软件的技术壁垒具有重要意义。与国外DPLR软件进行了对比研究，同时系统介绍了HyFLOW软件求解器的数值方法、物理化学模型以及壁面催化特性计算模型等主要方法，采用典型算例对有限催化模型进行了数值验证，最后基于LENS风洞试验146 mm返回器标模外形开展了高超声速气动热特性数值模拟。研究结果表明，HyFLOW软件在高超声速热化学非平衡流动模拟与评估方面的气动力计算精度高，与国外同类软件DPLR相当，同时其壁面催化条件下的气动热计算精度可靠，可信度高。

Simulation of aerothermal effects on reentry capsule geometry in LENS wind tunnel tests

The development of the National Numerical Windtunnel hypersonic flow simulation software HyFLOW is of huge significance in breaking the technical barriers of similar foreign software. A comparative study with the foreign DPLR software is conducted, and the main methods of the HyFLOW solver such as the numerical method, the physical and chemical models, and the calculation model of the wall catalytic characteristics are systematically introduced. Subsequently, numerical verification of the partial catalytic wall model is executed with a typical example, and finally the numerical simulation of the hypersonic aerothermal characteristics is performed based on the standard 146-mm reentry capsule model in the LENS wind tunnel test. The results show that the HyFLOW software has high aerodynamic calculation accuracy in simulation and evaluation of hypersonic thermochemical non-equilibrium flow, equivalent to that of the similar foreign DPLR software, while the calculation accuracy of aerodynamic heating under the wall catalytic conditions is reliable, with high credibility.