带喷流激波针流动特性实验研究

张江; 吴军飞; 尼文斌; 马汉东; 秦永明

doi:10.6052/0459-1879-16-020

带喷流激波针流动特性实验研究

中国航天空气动力技术研究院, 北京 100074

基金项目: 某总装共用技术基金资助项目.

详细信息

通讯作者:
张江,高级工程师,主要研究方向:空气动力学.E-mail:13611319903@163.com

中图分类号: V211.7
计量
- 文章访问数: 1062
- HTML全文浏览量: 97
- PDF下载量: 414
出版历程
- 收稿日期: 2016-01-12
- 修回日期: 2016-08-07
- 刊出日期: 2016-09-17

EXPERIMENTAL INVESTIGATION ON FLOWFIELD AROUND BLUNT BODY WITH FORWARD-FACING JET AND SPIKE

China Academy of Aerospace Aerodynamics, Beijing 100074, China

摘要

摘要: 采用动态测力、动态测压和纹影等风洞实验技术，对加装了带喷流激波针的钝头体的绕流特性、稳定和非稳模态的形成条件和机理进行了研究.结果表明：带喷流激波针流场存在稳态和非稳态两种模态，超声速喷流的压比大于临界压比时流动处于稳定模态，反之则为非稳模态；增大激波针长度可减小钝头体阻力，但达到一定长度后，进一步减阻的效果不再显著；增大喷流压比能够有效减弱再附激波强度，有利于缓解单独激波针的肩部热斑问题；非稳模态下波系自激振荡对再附激波在钝头体表面所围的区域影响剧烈，振荡是周期性的，且存在确定的主导频率，主导频率随喷流压力比增大而减小；自激振荡的产生是由于喷流出口周围的反压在喷流压比小于临界压比时无法获得持续的平衡而导致.
- 带喷流激波针 /
- 非稳模态 /
- 自激振荡 /
- 功率谱特性 /
- 减阻 /
- 风洞实验
Abstract: The characteristics of the flow around a blunt body with the combination of forward-facing jet and spike are investigated through wind tunnel experiments, which include the mechanism of steady mode and unsteady mode. The dynamic-force measurement, the dynamic-pressure measurement and the schlieren photograph are involved. The results indicate that there are the steady mode and the unsteady mode for the flow field around the blunt body with the combination of forward-facing jet and spike. The flow is steady as the pressure ratio of the supersonic jet is higher than the critical pressure ratio, while it is unsteady as the pressure ratio of the supersonic jet is lower than the critical pressure ratio. The drag of the blunt body decreases with the increasing of the length of the spike until the length of the spike reaches a certain value. With the enhancement of jet pressure ratio the strength of the reattachment shock waves is weakened significantly, which is beneficial to the eliminating of the hot spot on the shoulder of the blunt body. The pressure on the surface surrounded by the reattachment shock waves is fluctuating intensively under the unsteady mode, which is induced by the self-excited oscillations of shock waves around the blunt body. The dominant frequency of the self-excited oscillation decreases with the increasing of the jet pressure ratio. The mechanism of self-excited oscillation is that the ambient pressure around the jet exit cannot be balanced persistently when the jet pressure ratio is lower than the critical pressure ratio.
- combination of forward-facing jet and spike /
- unsteady mode /
- self-excited oscillation /
- power spectral characteristic /
- drag reduction /
- wind tunnel experiment

HTML全文

参考文献(30)

1 Hutt GR, Howe AJ. Forward facing spike effects on bodies of different cross section in supersonic flow. Aeronautical Journal, 1989, 93(926):229-234

2 罗喜胜, 翟志刚, 司廷等. 激波诱导下的气体界面不稳定性实验研究. 力学进展,2014, 44:201407(Luo Xisheng, Zhai Zhigang, Si Ting, et al. Experimental study on the interfacial instability induced by shock waves. Advances in Mechanics, 2014, 44:201407(in Chinese))

3 Ahmed MYM,Qin N. Surrogate-based multi-Objective aerothermodynamic design optimization of hypersonic spiked bodies. AIAA Journal, 2012, 50(4):797-810

4 培强. 三叉戟导弹的减阻空气锥. 现代军事, 1985, 1:23-29(Pei Qiang. Trident missile's air cone for drag reduction. Modern Military, 1985, 1:23-29(in Chinese))

5 Gauer M, Paull A. Numerical investigation of a spiked blunt nose cone at hypersonic speeds. Journal of Spacecraft and Rockets, 2008, 45(3):459-471

6 Meyer B, Nelson HF, Riggins DW. Hypersonic drag and heattransfer reduction using a forward-facing jet. Journal of Aircraft, 2001, 38(4):680-686

7 Yamauchi M, Fujii K, Higashino F. Numerical investigation of supersonic flows around a spiked blunt body. Journal of Spacecraft and Rockets, 1995, 32(1):32-42

8 Finley PJ. The flow of a jet from a body opposing a supersonic free stream. Journal of Fluid Mechanics, 1966, 26(2):337-368

9 何琨, 陈坚强, 董维中. 逆向喷流流场模态分析及减阻特性研究. 力学学报,2006,38(4):438-445(He Kun, Chen Jianqiang, Dong Weizhong. Penetration mode and drag reduction research in hypersonic flows using a counter-flow jet. Chinese Journal of Theoretical and Applied Mechanics, 2006, 38(4):438-445(in Chinese))

10 Josyula E, Pinney M, Blake WB. Applications of a counterflow drag reduction technique in high-speed systems. Journal of Spacecraft and Rockets, 2002, 39(4):605-614

11 Mehta RC. Numerical heat transfer study over spiked blunt bodies at Mach 6.8. J Spacecraft, 2000, 37(5):700-703

12 姜维, 杨云军, 陈河梧. 带减阻杆高超声速飞行器外形气动特性研究. 实验流体力学, 2011, 25(6):28-32(Jiang Wei, Yang Yunjun, Chen Hewu. Investigations on aerodynamics of the spike-tipped hypersonic vehicles. Journal of Experiments in Fluid Mechanics, 2011, 25(6):28-32(in Chinese))

13 Mehta RC. Heat transfer analysis over disc and hemispherical spike attached to blunt-nosed body at Mach 6. AIAA-2011-2228, 2011

14 Srinivasan GR, Chamberlain RR. Drag reduction of spiked missile by heat addition. AIAA-2004-4714, 2004

15 Josyula E, Pinney M, Blake WB. Applications of a counterflow drag reduction technique in high-speed systems. Journal of Spacecraft and Rockets, 2002, 39(4):605-614

16 耿云飞, 阎超. 联合激波针一逆向喷流方法的新概念研究. 空气动力学学报, 2010, 28(4):436-440(Geng Yunfei,Yan Chao. Numerical investigation on drag and heat-transfer reduction using combined spike and forward facing jet method. Acta Aerodynamica Sinica, 2010, 28(4):436-440(in Chinese))

17 张江,彭程,蔡琛芳等.基于响应面法的带喷流激波针参数优化研究.空气动力学学报,2015,33(2):204-210(Zhang Jiang, Peng Cheng, Cai Chenfang, et al. Optimization research on combination of spike and forward-facing jet using response surface methodology. Acta Aerodynamica Sinica, 2015, 33(2):204-210(in Chinese))

18 Morimoto N, Yoon JY, Aso S, et al. Reduction of aerodynamic heating with opposing jet through extended nozzle in high enthalpy flow. AIAA 2014-0705, 2014

19 Shang JS, Hayes J, Wurtzler K. Jet-spike bifurcation in high-speed flows. AIAA-00-2325, 2000

20 Shang JS, Hayes J, Wurtzler K. Flow oscillations of spike-tipped bodies. AIAA Journal, 1982, 20(1):25-26

21 Calarese W, Hankeyt WL. Modes of shock-wave oscillations on spike-tipped bodies. AIAA Journal, 1985, 23(2):185-192

22 Reding JP, Guenther RA, Jecmen D. Scale effects on the fluctuating pressures in a region of spike-induced flow separation. AIAA-79-0143, 1979

23 Feszty D, Badcock KJ, RichardsBryan E. Alleviation of airfoil dynamic stall moments via trailing-edge flap flow control. AIAA Journal, 2004, 42(1):95-106

24 Jagadeesh G, Viren M, Reddy KPJ. Hypersonic buzz phenomenon on the spiked blunt cones. In:41st Aerospace Sciences Meeting and Exhibit, Reno, January 6-9, 2003

25 Malmuth ND. Influence of a counterflow plasma jet on supersonic blunt body pressures. AIAA-99-4883, 1999

26 Fujita M. Axisymmetric oscillations of an opposing jet from a hemispherical nose. AIAA Journal, 1995, 33(10):1850-1856

27 Calarese W, Hankey WL. Modes of shock wave oscillations on spike-tipped bodies. AIAA-83-0544,1983

28 Guenther RA, Reding JP. Fluctuzting pressure environment of a drag reduction spike. AIAA-77-90,1977

29 Calarese W, Hankey WL. Modes of shock wave oscillations on spike-tipped bodies. AIAA-83-0544, 1983

30 Love ES, Grigsby CE, Lee LP, et al. Experimental and theoretical studies of axisymmetric free jets. NASA-TR-R-6, 1955

施引文献(4)

期刊类型引用(3)

1.	朱亮，李唯暄，李春雷，祁少波，田小涛. 逆向射流流场建立瞬态过程. 气体物理. 2023(04): 35-45 . 百度学术
2.	苑朝凯，李进平，陈宏，姜宗林，俞鸿儒. 高超声速溢流冷却实验研究. 力学学报. 2018(01): 1-8 . 本站查看
3.	王殿恺，文明，王伟东，卿泽旭. 脉冲激光与正激波相互作用过程和减阻机理的实验研究. 力学学报. 2018(06): 1337-1345 . 本站查看