高超声速飞行器表面横缝旋涡结构及气动热环境数值模拟  

Numerical investigation for vortexes and aerodynamic heating environment on transverse gap on hypersonic vehicle surface

作　　者：邱波[1,2] 张昊元 国义军[2] 曾磊[2] 石友安[2] 桂业伟[1,2] 

机构地区：[1]中国空气动力研究与发展中心空气动力学国家重点实验室,绵阳621000 [2]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《航空学报》2015年第11期3515-3521,共7页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(91216204);国家重点基础研究发展计划(2014CB744100)~~

摘　　要：针对高超声速飞行器表面横缝内部流动,通过求解可压缩Navier-Stokes方程,自主研发了一套能够较好模拟缝隙流动特性的CFD软件,利用该软件对横缝进行了数值模拟。研究表明,对于缝隙内黏性起主导作用的低速流动,通常需要密度足够充分的网格才能获得较好的计算结果。收敛后的壁面热流与文献实验热流吻合较好;缝隙内部旋涡个数近似与缝隙深宽比成比例,与文献中的有关结论完全一致。缝隙壁面热流分布受旋涡结构影响,会出现波浪式变化。因此,合理捕捉旋涡结构对于缝隙壁面热流的数值模拟有着重要意义,本文CFD软件对高超声速飞行器表面横缝的计算结果具有较高可信度。By solving the compressible Navier-Stokes equations,a CFD software is developed independently,which can well simulate the flow in the gap on the hypersonic vehicle surface.A numerical simulation research of transverse gap has been conducted with this software.The research shows that a preferable result comes from constructing grid with enough density to simulate the low-speed flow in the transverse gap.The convergent heat flux distribution is consistent with the experimental results in the previous literature;approximately,the number of the main vortexes in the gap is proportional to the depth-towidth ratio,which reaches agreement with findings in the literature as well.Affected by the vortexes,the heat flux distribution varies undulatingly.Therefore,capturing the vortexes reasonably has an important significance to the simulation of the heat flux and the results obtained from the CFD software are credible.

关 键 词：高超声速 缝隙 数值模拟 旋涡 热流分布 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]