二维喷管的初始流动

张焕好; 陈志华; 姜孝海

doi:10.13224/j.cnki.jasp.2015.09.016

二维喷管的初始流动

doi: 10.13224/j.cnki.jasp.2015.09.016

南京理工大学瞬态物理国家重点实验室, 南京 210094

基金项目:

国家自然科学基金(11272156)

国家自然科学基金青年科学基金(11502117)

详细信息

作者简介:
张焕好(1985-),女,广东中山人,讲师,博士生,主要从事计算燃烧与超声速流动研究.

中图分类号: V231.1
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- 被引次数: 0
出版历程
- 收稿日期: 2014-03-17
- 刊出日期: 2015-09-28

Initial flow of 2-D planer nozzle

Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing 210094, China

摘要

摘要: 基于可压缩Navier-Stokes方程,采用大涡模拟方法与高精度混合WENO/TCD格式,对Ma=1.4的超声速平面射流初始流场进行了数值研究.数值结果清晰地描述了超声速平面射流初始流场的结构特征,包括主涡环与激波结构以及它们演变过程.因主涡环内存在涡导激波对,激波与涡相互作用加速射流剪切层失稳,使剪切层首次卷起形成小涡的位置出现在涡导激波对后,此与亚声速射流情况不同.小涡串卷起成后,相继与涡导激波对相互作用,使激波出现明显的变形并加速主涡环失稳.
- 可压射流 /
- 涡环 /
- 激波 /
- 剪切层 /
- 激波与涡相互作用
Abstract: Based on the compressible Navier-Stokes equation, the initial flow structures of a supersonic planar jet at Ma=1.4 were investigated numerically with use of large eddy simulation (LES) and combination of the high-order hybrid WENO/TCD schemes. The numerical results illustrate clearly the initial flow characteristics of a supersonic planar jet, such as the generation and evolution of the main vortex ring and shock structures. Since the vortex-induced shock pair appears in the main vortex ring, the interaction of shock with vortex can accelerate the instability of jet shear layer, making the first roll up location differ from the subsonic case of just downstream the vortex-induced shock pair. After the vortexlets formation, the subsequent interactions with the vortex-induced shock pair would lead to a significant shape deformation of shock and accelerate the instability of main vortex ring.
- compressible jet /
- vortex ring /
- shock /
- shear layer /
- shock-vortex interaction

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参考文献(21)

[1]	张焕好,陈志华,孙晓晖.双管爆轰单引射增推机理的数值研究[J].航空动力学报,2011,26(5):1025-1030. ZHANG Huanhao,CHEN Zhihua,SUN Xiaohui.Numerical investigations on thrust augmentation mechanism of single ejection driven by two detonation tubes[J].Journal of Aerospace Power,2011,26(5):1025-1030.(in Chinese)
[2]	Alkislar M B,Choutapalli I,Krothapalli A,et al.The structure of a pulsed jet,a PIV study[R].AIAA-2005-1274,2005.
[3]	Zare-Behtash H,Kontis K,Takayama K.Compressible vortex loops studies in a shock tube with various exit geometries[R].AIAA-2008-362,2008.
[4]	Ishii R,Fujimoto H,Hatta N,et al.Experimental and numerical analysis of circular pulse jets[J].Journal of Fluid Mechanics,1999,392:129-153.
[5]	张丁午,王强,胡海洋.菱形孔射流在超声速流场中的气动特征[J].航空动力学报,2012,27(10):2378-2383. ZHANG Dingwu,WANG Qiang,HU Haiyang.Aerodynamic characteristics of sonic injection through diamond-shaped orifices in supersonic flow field[J].Journal of Aerospace Power,2012,27(10):2378-2383.(in Chinese)
[6]	Arakeri J H,Das D,Krothapalli A,et al.Vortex ring formation at the open end of a shock tube:a particle image velocimetry study[J].Physics of Fluids,2004,16(4):1008-1019.
[7]	Kopiev V F,Zaitsev M Y,Inshakov S I,et al.Visualization of the large-scale vortex structures in excited turbulent jets[J].Journal of Visualization,2003,6(3):303-311.
[8]	张焕好,陈志华,黄振贵,等.亚声速等膨胀平面射流的初始流场结构[J].推进技术,2012,33(4):591-596. ZHANG Huanhao,CHEN Zhihua,HUANG Zhengui,et al.Initial flow structures of aniso-expanded subsonic plane jet[J].Journal of Propulsion Technology,2012,33(4):591-596.(in Chinese)
[9]	Kontis K,An R,Edwards J A.Compressible vortex-ring interaction studies with a number of generic body configurations[R].AIAA-2005-1044,2005.
[10]	Zare-Behtash H,Kontis K,Gongora-Orozco N.Experimental investigations of compressible vortex loops[J].Physics of Fluids,2008,20(12):126105.1-126105.17.
[11]	Kitajima S,Iwamoto J,Tamura E.A study on the behavior of shock wave and vortex ring discharged from a pipe[R].Moscow:10th International Conference on Fluid Control,Measurements,and Visualization,2009.
[12]	Zhang H H,Chen Z H,Li B M,et al.The secondary vortex rings of a supersonic underexpanded circular jet with low pressure ratio[J].European Journal of Mechanics B:Fluids,2014,46:172-180.
[13]	张焕好,陈志华,黄振贵,等.超声速平面混合层小激波的形成与演变[J].计算力学学报,2012,29(5):772-778. ZHANG Huanhao,CHEN Zhihua,HUANG Zhengui,et al.The generation and evolution of shocklets in a supersonic plane mixing layer[J].Chinese Journal of Computational Mechanics,2012,29(5):772-778.(in Chinese)
[14]	Voelkl T,Pullin D I,Chan D C.A physical-space version of the stretched-vortex subgrid-stress model for large-eddy simulation[J].Physics of Fluids,2000,12(7):1810-1825.
[15]	Lundgren T S.Strained spiral vortex model for turbulent fine structure[J].Physics of Fluids,1982,25(12):2193-2203.
[16]	Hill D J,Pullin D I.Hybrid tuned center-difference-WENO method for large eddy simulations in the presence of strong shocks[J].Journal of Computational Physics,2004,194(2):435-450.
[17]	Pantano C,Deiterding R,Hill D J,et al.A low numerical dissipation patch-based adaptive mesh refinement method for large-eddy simulation of compressible flows[J].Journal of Computational Physics,2007,221(1):63-87.
[18]	Zhao W,Frankel S H,Mongeau L G.Effects of trailing jet instability on vortex ring formation[J].Physics of Fluids,2000,12(3):589-596.
[19]	Giles M B.Non-reflecting boundary conditions for Euler equation calculations[J].AIAA Journal,1990,28(12):2050-2058.
[20]	Hillier R.Computation of shock wave diffraction at a ninety degrees convex edge[J].Shock Waves,1991,1(2):89-98.
[21]	Grasso F,Pirozzoli S.Shock-wave-vortex interactions:shock and vortex deformations,and sound production[J].Theoretical and Computational Fluid Dynamics,2000,13(6):421-456.