摘要
高超声速非平衡流动气动加热的精确预测是当前高超声速飞行器热防护设计面临的难点和热点问题.设计了外形简单的球柱测热模型,采用表面溅射金Au和二氧化硅SiO_2的方法改变了模型和塞式量热计表面的催化特性,并在电弧风洞中开展了高超声速非平衡流动气动加热试验,获得了近完全催化壁及近非催化壁两种条件下模型表面的气动加热数据.通过和数值模拟结果对比分析,对高温化学非平衡气动加热的数值预测方法进行了验证,结果表明:表面材料的催化特性对非平衡气动加热有显著影响,测热模型的球面上催化效应影响明显,完全催化热流要高于非催化热流,而柱面上催化效应较弱;数值模拟得到的不同壁面催化条件之间热流差异大于地面试验结果;计算结果与试验结果相比,完全催化壁热流相差在5%以内,完全非催化壁热流相差超过10%.
In the design of hypersonic vehicle thermal protection, precise prediction on the non-equilibrium aerodynamic heating in condition of hypersonic flow has been recognized as the difficult and hot topic in the current academic and engineering field. In this paper, a simple spherical column thermal model was designed. The surface catalytic properties of the model and plug-type calorimeter were changed by sputtering Au and Si O2 on the surface. In the arc tunnel, a hypersonic non-equilibrium flow aerodynamic heating test was carried out to obtain the aerodynamic heating data of the model surface under both near complete catalysis and near non-catalysis.Based on the comparative analysis of test results and numerical calculation results, the numerical prediction method of high temperature chemical non-equilibrium aerodynamic heating is validated. The results show that the catalytic properties of the surface material have a significant effect on the non-equilibrium aerodynamic heating; the catalytic effect on the spherical surface is obvious,the complete catalytic heating is higher than the non-catalytic heating, but the catalytic effect on the cylinder surface is weaker. The numerical simulation results show that the difference of the heat flux between the different wall catalytic conditions is greater than that of the ground test results; completely catalytic wall heat flux within 5% of the difference, completely non-catalytic wall heat flux difference of more than 10%.
引文
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