超声速气流中多孔逆向射流减阻防热机理研究

为提高高超声速飞行器头部的减阻防热性能,对钝化前缘多孔逆向射流方案进行参数化研究。基于雷诺平均三维可压缩N-S方程,采用SST k-ω湍流模型对流场进行数值仿真,通过与公开文献中的实验数据进行对比,验证了数值方法的可靠性。重点对比分析了有无多孔逆向射流方案下钝化前缘的流场结构,多孔逆向射流的引入使飞行器头部流场发生变化,将飞行器头部前缘的弓形激波向外推移,使前缘展向壁面处于一个连续的低温环境中。结果表明,多孔逆向射流在减阻和热防护方面均能起到良好效果。

Study on Drag Reduction and Thermal Protection Mechanism of the Porous Opposing Jet in Hypersonic Flow

The numerical study about the porous opposing jet scheme on the leading edge of blunt body is conducted to improve the drag reduction and thermal protection on the head of hypersonic vehicle. The three dimensional compressible Reynolds Averaged Navier-Stokes(RANS) equations and SST k-ω turbulence model are used to perform numerical simulation in the flow. The reliability of the numerical method is verified by comparing with the experimental data from the published iterature. The flow field structure of the leading edge of blunt body with the porous opposing jet or not is compared and analysis mainly. The introduction of the porous opposing jet changes the flow field of the vehicle head, pushes the bow shock wave at the leading edge of the vehicle head outward and makes the leading edge extending to the wall surface in a low temperature environment continually. The results show that the porous opposing jet has good effect in both drag reduction and thermal protection.