高超声速激波边界层相互干扰的数值研究
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- 英文论文题名：Simulation of Shock Wave and Boundary Layer Interaction in Hypersonic Flow
- 论文作者：张小莉 ; 张一帆 ; 谭伟伟 ; 梁益华
- 英文论文作者：Zhang Xiaoli ; Zhang Yifan ; Tan Weiwei ; Liang Yihua ; Aeronautics Computing Technique Research Institute Xi'an
- 年：2016
- 作者机构：中航工业西安航空计算技术研究所;
- 论文关键词：激波边界层干扰 ; 高超声速 ; 非对称交叉激波 ; 压缩拐角
- 英文论文关键词：shock wave-boundary layer interaction ; hypersonic ; 3-D Double Fin ; compression corner
- 会议召开时间：2016-10-31
- 会议录名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛文集（下册）
- 英文会议录名称：Discovery,Innovation and Communication——Proceedings of 7th CSAA Science and Technology Youth Forum
- 语种：中文
- 分类号：V211
- 学会代码：ZGHU
- 会议名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛
- 会议地点：中国广东中山
- 主办单位：中国航空学会
- 学会名称：中国航空学会
- 页数：5
- 文件大小：2974k
- 原文格式：O
- 会议级别：全国
摘要
激波与边界层相互干扰是高超声速流动研究的关键技术之一,为了实现对此类问题的准确数值模拟,采用基于有限体积法的非结构网格软件,对激波入射、16°压缩拐角、非对称交叉激波三个典型高超软件验证算例进行了研究,并与实验结果进行了对比分析。结果表明:计算的物面压力、摩阻与试验结果吻合的比较好;空间离散格式、湍流模型对壁面压力和摩阻的影响很小;总的来看,S—A湍流模型的计算结果比其SST稍好一些。从得到的结果看.该软件能够较为准确模拟高超声速飞行器的气动力问题。
The interaction between shock wave and boundaiy layer of hypersonic flow is studied in this paper.A solver using hybrid grid based finite volume method is used for accurate prediction of aerodynamic force.In this paper,three test cases are computed by the code,which are shock impingement、 compression corner and 3-D double Fin.As compared with the experiment,the computed surface pressure and skin friction are very good,turbulence model and spatial discretization has little effect on aerodynamics;S-A model results are a bit of better than SST model.It showed that the code can provide reliable numerical data for hypersonic vehicle aerodynamic design.
The interaction between shock wave and boundaiy layer of hypersonic flow is studied in this paper.A solver using hybrid grid based finite volume method is used for accurate prediction of aerodynamic force.In this paper,three test cases are computed by the code,which are shock impingement、 compression corner and 3-D double Fin.As compared with the experiment,the computed surface pressure and skin friction are very good,turbulence model and spatial discretization has little effect on aerodynamics;S-A model results are a bit of better than SST model.It showed that the code can provide reliable numerical data for hypersonic vehicle aerodynamic design.
引文
[1]李世珍,唐硕.高超声速进气道壁面开缝对边界层分离影响研究[J].空气动力学学报,2011,29(2):68-73.
[2]高飞飞,田增冬,刘沙.双椭球和Edney-type IV激波干扰的高速流动数值模拟[J].信息通信,2016,3(159).
[3]刘周,杨云军,周伟江.高超声速激波/边界层干扰流动数值模拟研究龚安龙[J].空气动力学学报,2014,32(6).
[4]Knight D.Test cases for CFD validation of hypersonic flight[R].RTO-TR-AVT-007-V3,2006.
[5]A B Oliver,R P Lillard.Validation of High-Speed Turbulent Boundary Layer and Shock-Boundary Layer Interaction Computations with the OVERFLOW Code,AIAA,2006-0894,2006.
[6]贺旭照,赵慧勇,乐嘉陵.吸气式高超声速飞行器气动力气动热的数值模拟方法及应用[J].计算物理,2008,25(5).
[7]赵慧勇,雷波,乐嘉陵.非对称交叉激波和湍流边界层相互作用的数值研究[J].航空动力学报,2009,24(10).
[2]高飞飞,田增冬,刘沙.双椭球和Edney-type IV激波干扰的高速流动数值模拟[J].信息通信,2016,3(159).
[3]刘周,杨云军,周伟江.高超声速激波/边界层干扰流动数值模拟研究龚安龙[J].空气动力学学报,2014,32(6).
[4]Knight D.Test cases for CFD validation of hypersonic flight[R].RTO-TR-AVT-007-V3,2006.
[5]A B Oliver,R P Lillard.Validation of High-Speed Turbulent Boundary Layer and Shock-Boundary Layer Interaction Computations with the OVERFLOW Code,AIAA,2006-0894,2006.
[6]贺旭照,赵慧勇,乐嘉陵.吸气式高超声速飞行器气动力气动热的数值模拟方法及应用[J].计算物理,2008,25(5).
[7]赵慧勇,雷波,乐嘉陵.非对称交叉激波和湍流边界层相互作用的数值研究[J].航空动力学报,2009,24(10).