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本文针对高超声速再体的烧蚀现象 ,利用简单隐式TVD差分格式和激波捕捉法 ,数值求解三维化学非平衡Navier Stokes方程 ,其中化学模型是碳 碳 (C C)空气化学模型 ,考虑 12个化学组分和 31个化学反应过程 ,研究了C C烧蚀对再入体头部区域的壁面温度和热流分布的影响。为了计算效率和稳定性提出壁面条件显式处理的方法。对再入高度为 6 5km和速度为 8km/s的再入体头部区域烧蚀流场进行了数值模拟 ,用飞行迎角α =0°的计算结果与国外文献进行了比较 ,符合得较好。同时给出了三维小迎角α =5°的计算结果
In this paper, a three-dimensional chemical unbalanced Navier Stokes equation is numerically solved by the simple implicit TVD difference scheme and the shock capture method. The chemical model is a carbon-carbon (CC) air chemistry model. Considering 12 Chemical composition and 31 chemical reaction processes, the effects of CC ablation on the wall temperature and heat flow distribution in the reentry head area were studied. In order to calculate the efficiency and stability of the proposed wall conditions explicit treatment method. The ablation flow field in reentry head region with a re-entry height of 65 km and a velocity of 8 km / s was numerically simulated. Comparing with the foreign literature, it is good. At the same time, the calculation results of three-dimensional low angle of attack α = 5 ° are given