三维非对称斜劈高速流动计算方法研究  

Computational Methods of High Speed Flow on Three-dimensional Asymmetrical Double-fin

作　　者：聂智军[1] 田增冬[1] 成水燕[1] 谭伟伟[1] 

机构地区：[1]中航工业西安航空计算技术研究所,陕西西安710068

出　　处：《航空计算技术》2014年第2期18-21,共4页Aeronautical Computing Technique

基　　金：国家"863"计划项目资助(2012AA01A304)

摘　　要：交叉激波是高超声速进气道发展的关键气动问题之一。为实现对此类高速流动的准确数值模拟,基于RANS方程的自研多块结构网格计算软件,对经典三维非对称斜劈构型的斜激波交叉干扰流动特征开展了计算研究。通过对比分析,系统评估了计算网格、湍流模型及高精度格式对空间流场、底板摩擦力流线、压强分布、绝热壁温分布等的影响,获得了适用于三维非对称高速流动问题的网格生成准则和计算策略,同时验证了自研软件的模拟能力。Crossing shock wave is one of the key aerodynamic problems for the development of hypersonic inlet.In order to realize accurate numerical simulation for such high speed flow ,computational study is performed on the oblique shock wave interference flow characteristic of three-dimensional asymmetrical double-fin,based on in-house multi-block structured grid solver of RANS equation .Through contrasting and analyzing ,the effects of computing mesh ,turbulence models and high precision format on spatial flow-field,friction force streamline of the soleplate ,pressure distribution ,the adiabatic wall temperature distri-bution are systematically evaluated .Mesh generation rules and computational strategy adapted to three-di-mensional asymmetrical high-speed flow are obtained .The in-house solver simulation capability for this kind of flow is validated .

关 键 词：RANS 高速流动 非对称 网格生成准则 计算策略 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]