高超声速飞行器在特定工况下飞行时，其表面会存在湍流与化学非平衡耦合作用，但考虑化学反应的高温湍流边界层的研究工作还十分有限。本文选取高超声速楔形体头部斜激波后的流动状态，分别采用热完全气体模型、空气化学反应模型开展直接数值模拟研究，对比分析了化学非平衡效应对湍流统计量、湍流脉动量的影响趋势，并研究了高温湍流边界层标度律。计算结果表明，以吸热离解反应为主的化学非平衡效应会使得边界层平均温度和脉动温度显著降低，但对平均速度剖面、速度脉动、雷诺应力的影响较小；在高温化学非平衡湍流边界层的对数区，各流动参数的拓展自相似理论的相对标度指数基本符合标度律。

Under the specific flying condition, the interaction between turbulence and chemical nonequilibrium will exist on the surface of the vehicles, but the related research is still very limited. The flow state after the leading shock of a cone is chosen, and two gas models, i.e. the calorically perfect gas and the chemical reaction gas are utilized for the DNS study. The effects of chemical nonequilibrium on the turbulence statistics and fluctuations are analyzed, and the scaling law are investigated. The results show that the endothermic dissociated reaction is dominant in the boundary layer, which leads to the significant decreasing of the averaged-temperature and temperature fluctuation. But the effects of chemical nonequilibrium only have a little influence on the averaged streamwise velocity, velocity fluctuation and Reynold stress. In the log-region, the ESS of the fluctuations are still consistent with the scaling law.