局部多孔壁－内腔结构的气动加热瞬态特性

根据超声速飞行器外表面连接结构处密封结构几何特征，以局部多孔壁和内腔结构为研究对象，建立流/固/多孔区域流动和传热过程耦合计算模型，其中多孔区域中运用分布阻力法，流、固区域间换热过程采用准稳态耦合计算方法。经过与相关实验数据进行对比，验证了程序可靠性，并进一步分析在整个长时间瞬态过程中，该密封结构的流动和传热特征，阐明了在瞬态过程中多孔材料等效热流对缝隙壁面的加热作用。研究了有、无多孔材料填充两种情况下缝隙壁面热流分布形态的差异，探讨了缝隙中填充多孔材料对高速流场边界层热气流侵入内腔过程的影响。

Transient Characteristics of Aerodynamically Heating Partial Porous Wall-Inner Cavity

According to the geometric characteristics of seal structure in the joint location of the supersonic vehicle surface,taking the partial porous wall and the cavity as the research object,the fluid flow/heat transfer coupled computational model in fluid/solid/porous areas is established.The distributed resistance method is utilized in the porous media and the quasi steady coupled method is utilized in the heat transfer process between fluid and solid areas.The compilling program is testified to be feasible by comparing its results with the correlated experimental data.Then,flow and heat transfer characteristics in the seal structure are analyzed during a longer transient process.In the transient process,the heating effect of the equivalent heat flux of the porous material on the slot wall are illustrated.The distributing differences with and without porous material stuffed are studied.The effects of the porous material on the process that the boundary thermal flow in the high speed flow field invades into the inner cavity are investigated.