凹型粗糙元对边界层稳定性的影响

刘开平; 罗纪生

doi:10.13224/j.cnki.jasp.2016.01.022

凹型粗糙元对边界层稳定性的影响

doi: 10.13224/j.cnki.jasp.2016.01.022

天津大学机械工程学院力学系, 天津 300072

基金项目:

国家自然科学基金(11332007)

详细信息

作者简介:
刘开平(1985-),男,辽宁大连人,硕士生,主要从事层流-湍流转捩和流动稳定性的研究.

中图分类号: V211.3
计量
- 文章访问数: 802
- HTML浏览量: 3
- PDF量: 492
- 被引次数: 0
出版历程
- 收稿日期: 2014-05-08
- 刊出日期: 2016-01-28

Effect of concave groove on the stability of boundary layer

Department of Mechanics, School of Mechanical Engineering, Tianjin University, Tianjin 300072, China

摘要

摘要: 为了能够利用e^N方法对带有凹型粗糙元的平板边界层进行转捩预测.通过数值模拟和流动稳定性的方法研究了马赫数为4.5的超声速边界层中凹型粗糙元对扰动演化的影响.对两种尺度的凹型粗糙元下扰动沿流向的幅值和增长率分布进行了计算.结果表明:凹型粗糙元对基本流的影响只是局限在凹型粗糙元及其附近很小的范围内.凹型粗糙元对扰动幅值的演化有抑制作用,尺度越大抑制作用越明显.在凹型粗糙元的后面,凹型粗糙元对扰动幅值的增长率的影响很小,相对变化量在2%以内.验证了对壁面有凹型粗糙元的情况,可以通过流动稳定性分析加N值修正的方法进行转捩预测.
- 转捩预测 /
- 边界层 /
- 局部扰动 /
- 凹型粗糙元 /
- 流动稳定性 /
- e^N方法
Abstract: In order to predict the transition position using e^N method for flat boundary layer with concave groove, the effects of concave groove on the evolution of disturbance in supersonic boundary layer with Mach number of 4.5 were studied by numerical simulation and flow stability method. The amplitude and growth rate distribution along the flow direction with two sizes of concave groove was revealed. The results show that the range of effect of concave groove on the basic flow is only limited in the concave groove and near range. Concave groove has a suppressed effect on the evolution of disturbance to some extent, the bigger size means the more obvious inhibitory effect. After concave groove, the effect of concave groove on the growth rate of disturbance amplitude is little, and relative variation is smaller than 2%.At the same time, the position of transition can be predicted more accurately with a smaller concave groove by e^N method combined with stability analysis and a correction factor of N.
- transition prediction /
- boundary layer /
- local disturbance /
- concave groove /
- flow stability /
- e^N method

HTML

参考文献(19)

[1]	黄志澄.空天飞机的边界层转捩[J].气动实验与测量控制,1994,8(1):1-9. HUANG Zhicheng.Boundary layer transition for aerospace plane[J].Aerodynamic Experiment and Measurement and Control,1994,8(1):1-9.(in Chinese)
[2]	Liepmann H W,Fila G H.Investigations of effects of surface temperature and single roughness elements on boundary-layer transition[R].NACA Report 890,1947.
[3]	Smith A M O,Clutter D W.The smallest height of roughness capable of affecting boundary-layer transiton[J].Journal of the Aerospace Sciences,1959,26(4):229-245.
[4]	Gao B,Park D H,Park S O.Stability analysis of a boundary layer over a hump using parabolized stability equations[J].Fluid Dynamics Research,2011,43(5):1-19.
[5]	Holloway P F,Sterrett J R.Effect of controlled surface roughness on boundary-layer transition and heat transfer at Mach numbers of 4.8 and 6.0[R].NASA TN-D-2054,1964.
[6]	陆昌根,赵玲慧,沈露予.局部扰动对平板边界层流动稳定性影响的研究[J].空气动力学学报,2012,30(1):63-67. LU Changgen,ZHAO Linghui,SHEN Luyu.Influence of local disturbance on the stability of boundary layer[J].Acta Aerodynamica Sinica,2012,30(1):63-67.(in Chinese)
[7]	李慧.单个粗糙元对可压缩平板边界层稳定性影响的研究[D].天津:天津大学,2013. LI Hui.The effect of single roughness element on the stability in a compressible boundary layer on a flat plate[D].Tianjin:Tianjin University,2013.(in Chinese)
[8]	陈金,陈方,刘洪.超临界翼型加装鼓包减阻的数值研究及优化设计[J].微型电脑应用,2011,27(2):1-3. CHEN Jin,CHEN Fang,LIU Hong.The optimization design and numerical study of drag-reducing using bumps on supercritical wings[J].Microcomputer Applications,2011,27(2):1-3.(in Chinese)
[9]	杨洋,陈迎春,黄炜.跨音速机翼采用鼓包主动减阻技术研究[J].民用飞机设计与研究,2012,28(2):13-17. YANG Yang,CHEN Yingchun,HUANG Wei.Active drag-reducing technique using bumps on transonic wings[J].Civil Aircraft Design and Research,2012,28(2):13-17.(in Chinese)
[10]	蔡巧言,谭慧俊.前体边界层状态对高超声速进气道流动结构及性能的影响[J].航空动力学报,2008,23(4):699-705. CAI Qiaoyan,TAN Huijun.Effects of the fore-body boundary layer state non flow structure and performance of hypersonic inlets[J].Journal of Aerospace Power,2008,23(4):699-705.(in Chinese)
[11]	赵慧勇,周瑜,倪鸿礼,等.高超声速进气道边界层强制转捩实验[J].实验流体力学,2012,26(1):1-6. ZHAO Huiyong,ZHOU Yu,NI Hongli,et al.Test of forced boundary-layer transition on hypersonic inlet[J].Journal of Experiments in Fluid Mechanics,2012,26(1):1-6.(in Chinese)
[12]	Smith A M O,Gamberoni N.Transition pressure gradient and stability theory[R].Long Beach,California:Douglas Aircraft Company Report ES26388,1956.
[13]	Van Ingen J L.A suggested semi-empirical method for the calculation of the boundary layer transition region[R].Delft,Netherland:Aerospace Engineering Report VTH-74,1956.
[14]	Malik M R,Orszag S A.Comparison of methods for prediction of transition by stability analysis[J].AIAA Journal,1980,18(12):1485-1489.
[15]	苏彩虹,周恒.小攻角高超音速尖锥边界层的转捩预测及e^N法的改进[J].中国科学,2009,39(1):123-130. SU Caihong,ZHOU Heng.The transition prediction of hypersonic boundary-layer with a small angles of attack and the improvement of e^N[J].Science in China,2009,39(1):123-130.(in Chinese)
[16]	吴宁宁,罗纪生.壁面小折角对马赫数4.5边界层中扰动演化的影响[J].空气动力学学报,2014,32(2):219-227. WU Ningning,LUO Jisheng.The effect of small wall-angle on the evolution of disturbances in the boundary layer of Mach number 4.5[J].Acta Aerodynamica Sinica,2014,32(2):219-227.(in Chinese)
[17]	张华,罗纪生.用扰动方程研究可压缩流动边界层中扰动的演化[J].燕山大学学报,2007,30(3):248-252. ZHANG Hua,LUO Jisheng.The study of evolution of perturbations in the compressible boundary layer flow using perturbation equations[J].Journal of Yanshan University,2007,30(3):248-252.(in Chinese)
[18]	刘建新,罗纪生.小攻角高超声速钝锥边界层中不同扰动对转捩的影响[J].应用数学和力学,2010,31(5):505-515. LIU Jianxin,LUO Jisheng.Effect of disturbances at inlet on hypersonic boundary layer transition on a blunt cone at small angle of attack[J].Applied Mathematics and Mechanics,2010,31(5):505-515.(in Chinese)
[19]	安德森.计算流体力学基础及其应用[M].吴松平,刘赵淼,译.北京:机械工业出版社,2007.