航空计算技术
航空計算技術
항공계산기술
AERONAUTICAL COMPUTER TECHNIQUE
2014年
2期
18-21
,共4页
聂智军%田增冬%成水燕%谭伟伟
聶智軍%田增鼕%成水燕%譚偉偉
섭지군%전증동%성수연%담위위
RANS%高速流动%非对称%网格生成准则%计算策略
RANS%高速流動%非對稱%網格生成準則%計算策略
RANS%고속류동%비대칭%망격생성준칙%계산책략
RANS%high-speed flow%asymmetry%mesh generation rules%computational strategy
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。
交扠激波是高超聲速進氣道髮展的關鍵氣動問題之一。為實現對此類高速流動的準確數值模擬，基于RANS方程的自研多塊結構網格計算軟件，對經典三維非對稱斜劈構型的斜激波交扠榦擾流動特徵開展瞭計算研究。通過對比分析，繫統評估瞭計算網格、湍流模型及高精度格式對空間流場、底闆摩抆力流線、壓彊分佈、絕熱壁溫分佈等的影響，穫得瞭適用于三維非對稱高速流動問題的網格生成準則和計算策略，同時驗證瞭自研軟件的模擬能力。
교차격파시고초성속진기도발전적관건기동문제지일。위실현대차류고속류동적준학수치모의，기우RANS방정적자연다괴결구망격계산연건，대경전삼유비대칭사벽구형적사격파교차간우류동특정개전료계산연구。통과대비분석，계통평고료계산망격、단류모형급고정도격식대공간류장、저판마찰력류선、압강분포、절열벽온분포등적영향，획득료괄용우삼유비대칭고속류동문제적망격생성준칙화계산책략，동시험증료자연연건적모의능력。
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 .
