期刊文献+

细长体大攻角非对称分离的数值模拟研究 被引量:2

Numerical Simulation Study on Asymmetry Detached Flow of a Slender Body at High Angles of Attack
下载PDF
导出
摘要 对于旋成体大攻角非对称分离进行数值模拟。通过对DES方法和RANS方法模拟细长体非对称分离流动不同结果的比较,揭示了DES方法在大攻角分离流动模拟方面具有明显的优势,能充分模拟出大攻角分离的非对称特性。通过对比研究,说明DES方法是适合细长体非对称分离研究的数值方法。 The numerical simulation means on asymmetry detached flow of a slender at high angles of attack are analysed. Companring the different result simulated by Detached-Eddy Simulation (DES) and Reynolds-averaged Navier-Stokes (RANS) for the asymmetry detached flow around a slender, DES has more advantageous for the separated flow simulation at high incidence and can simulate efficiently flow asymmetry. The result shows that DES is a more effective numerical simulation means for currently research.
作者 张利锋 李栋
出处 《科学技术与工程》 2008年第8期2272-2275,共4页 Science Technology and Engineering
基金 国家自然科学基金(10772149)资助
关键词 细长体 大攻角 非对称分离 DES方法 slender body high incidence asymmetry detached flow DES approach
  • 相关文献

参考文献8

  • 1[2]Ericsson L E.Vortex unsteadiness of slender bodies at high incidence.Journal of Spacecraft and Rockets,1987;
  • 2[3]Hall R M.Forebedy and missile side forces and the time analogy.AIAA paper 87-0327,1987
  • 3[4]Spalart P R.Jou W H,StreletsM.et al.Comments on the feasibility of LES for wings,and on a hybrid RANS/LES approach.lst AFOESR Int,Conf on DNS/LES,Ruston LA In Liu C,Liu Z Eds.Advances in DES/LES,Greyden Press,Columbus,OH,1997
  • 4[5]Li D M.Nakamura Y.Detached-eddy simulation of three airfoils with different
  • 5[6]stall onset mechanisms.Journal of Aircraft,2006;43(4):
  • 6[7]Moron S,Fomythe J R,Mitchell A.et al.DES and BANS simulations of delta wing vortical flows.AIAA Paper 2002-0587,2002
  • 7[8]Forsythe J R,Hoffmann K A,Squires K D.Detached-eddy simulation with compressibility comprections applied to a supersonic axisymmetric base flow.AIAA Paper 02-0586,2002
  • 8[9]Spalart P R,Allmaras S R,A one-equation turbulence model for aerodynamic flows,AIAA Paper 92-0439,1992

同被引文献22

  • 1刘仙名,符松.用可实现k-ε模式对细长体大攻角分离流场的数值模拟[J].计算力学学报,2006,23(3):275-279. 被引量:8
  • 2管小荣,徐诚.细长体大攻角非对称涡流的数值研究[J].弹道学报,2007,19(1):55-58. 被引量:5
  • 3邓学蓥 王刚 陈学锐 等.细长体大迎角流动的确定性和多涡系结构的研究[A]..全国第九届分离流?旋涡和流动控制会议论文集[C].北京,2002年8月..
  • 4张涵信,冉政.细长锥体有攻角绕流对称流态到非对称流态的结构稳定性研究[J].空气动力学学报,1997,15(1):20-26. 被引量:12
  • 5Wilcox F J,Jr;Birch T J, Allen J M. Force, surface pressure and flowfield measurements on slender missiles configurations at supersonic speeds [ C]//18th AIAA Applied Aerodynamics Conference, 2000.
  • 6Josyula E. Computational simulation improvements of supersonic high-angle-of-attack missile flows [ J ]. Journal of Spacecraft and Rockets, 1999, 36 (1).
  • 7Ericsson L E, Beyers M E. Forebody flow control at conditions of naturally occurring separation asymmetry. J Aircraft, 2002, 39:252-261.
  • 8David D, Murray T. Effect of upstream disturbance on flow asymmetry. In: 30th Aerospace Sciences Meeting and Exhibit, Aerospace Sciences Meetings, 1992, Reno, NV, USA. AIAA-1992-0408.
  • 9Meng X S, Jia C, Qiao Z D, et al. Development of flow asymmetry with angle of attack over a 20° circular cone at low speed. In: 37th AIAA Fluid Dynamics Conference and Exhibit, 25-28, June, 2007, Miami, Florida. AIAA-2007-4118.
  • 10袁先旭.非定常流动数值模拟及飞行器动态特性分析研究.博士学位论文.绵阳:中国空气动力研究与发展中心研究生部.2002.

引证文献2

二级引证文献4

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部