Comparison of Strategies for Coupled Flow‑Thermal Analysis of Thermal Protection System at Hypersonic Flight Condition
Comparison of Strategies for Coupled Flow‑Thermal Analysis of Thermal Protection System at Hypersonic Flight Condition
复制标题
耦合流策略比较——高超声速飞行工况热防护系统热分析
DOI：
10.1007/s42405-019-00217-x
复制
发表时间：
2019
影响因子：
1.7
通讯作者：
Hongwei Song
中科院分区：
文献类型：
--
作者：
Ruixing Wang;Zhaowei Wang;Hongwei Zheng;Hongwei Song
流热耦合分析是高超声速飞行器性能评估和结构设计的关键。本文针对实际工程中吸气式高超声速飞行器的流热耦合响应问题，提出了几种计算策略，并进行了比较。首先，提出了通过壁面温度和恢复温度修正壁面热流的基本直接修正方法，有效地近似了流热效应。其次，通过插值相邻轨迹点之间的冷壁热流和恢复温度，进一步发展了改进的DCM（IDCM），以提高计算精度。第三，迭代求解方法（ISM），通过质量和能量平衡在一个共同的接口之间的CFD分析程序和CSD分析程序的迭代求解。以吸气式高超声速飞行器为算例，比较了热响应和流动特性。结果表明，DCMs和ISM的热响应趋势是一致的。然而，对于DCM，热壁对流动特性的影响被忽略，而ISM充分考虑，因此，增厚的边界流动和复杂的内部流动可以捕获。然而，在比较计算效率时，由于解耦算法和并行策略，DCM比ISM具有突出的优势。基于此，在吸气式高超声速飞行器的实际设计过程中，设计人员可以根据不同的设计阶段选择合适的流热分析方法。
Coupled flow-thermal analysis is crucial for the performance evaluation and structural design of hypersonic vehicles. In this study, several strategies for computing the coupled flow-thermal response of air-breathing hypersonic flights in practical engineering are developed and compared. First, the basic direct correction method that amends wall heat flux via recovery temperature and wall temperature is proposed to approximate flow-thermal effects efficiently. Second, the improved DCM (IDCM) is further developed by interpolating the cold wall heat flux and the recovery temperature between adjacent trajectory points to improve computational accuracy. Third, the iteration solution method (ISM) that obtains solutions through mass and energy balances at a common interface by iterations between CFD analysis code and CSD analysis code is also presented. Thermal response and flow characteristics are compared through a test case of an air-breathing hypersonic vehicle. The results show that the thermal response tendencies are consistent by DCMs and ISM. However, for DCMs, the impact of hot wall on the flow characteristics is ignored, whereas it is fully considered in ISM; thus, the thickened boundary flow and complicated internal flow can be captured. However, while comparing computational efficiency, DCMs have a prominent advantage over ISM due to the decoupling algorithm and parallel strategy. Based on this, in the actual design process of an air-breathing hypersonic vehicle, the designers can select the proper flow-thermal analysis method according to the different design stages.