北京航空航天大学学报 ›› 2019, Vol. 45 ›› Issue (3): 624-632.doi: 10.13700/j.bh.1001-5965.2018.0409

• 论文 • 上一篇    下一篇

类X-51A飞行器非定常湍流精细模拟

余华峰, 刘宏康, 陈树生, 阎超   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100083
  • 收稿日期:2018-07-09 出版日期:2019-03-20 发布日期:2019-04-04
  • 通讯作者: 阎超,E-mail:05642@buaa.edu.cn E-mail:05642@buaa.edu.cn
  • 作者简介:余华峰,男,硕士研究生。主要研究方向:湍流模拟;阎超,男,博士,教授,博士生导师。主要研究方向:计算流体力
  • 基金资助:
    国家自然科学基金(11721202)

High-resolution unsteady turbulence simulation of an X-51A-like aircraft

YU Huafeng, LIU Hongkang, CHEN Shusheng, YAN Chao   

  1. School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China
  • Received:2018-07-09 Online:2019-03-20 Published:2019-04-04

摘要: 针对类X-51A飞行器在超声速大迎角状态下存在的大范围非定常分离流动,开展了精细化湍流数值模拟研究。计算基于高阶格式下的延迟分离涡模拟方法(DDES),来流马赫数为2.5,迎角为10°。分析了该复杂流场中存在的分离流动现象、分离流动诱导的气动特性变化规律以及压力脉动特点;其中重点研究了壁面压力脉动强度分布情况和监测点压力脉动频谱特性。分析结果表明:飞行器大迎角飞行时从侧缘诱导出明显的分离涡,并对尾部舵面产生干扰;受干扰尾舵表现出明显的非线性及非定常气动特性;分离涡的存在导致飞行器尾舵前缘等位置的壁面压力脉动显著增强,200~300 Hz的低频高幅值脉动可能会导致结构破坏。

关键词: 非定常, 分离流动, 压力脉动, 延迟分离涡模拟(DDES), 数值模拟

Abstract: High-resolution turbulence simulations were performed for an X-51A-like aircraft model to investigate its complex unsteady separation flow caused by high angle of attack conditions. The calculation is based on delayed detached-eddy simulation (DDES) methodology under high order. Flow Mach number is 2.5, and the angle of attack is 10°. In this paper, separation flow phenomenon, separation flow induced aerodynamic characteristic variation law and pressure fluctuation features are analyzed. Especially, the distribution of wall pressure fluctuation and the spectrum characteristics of the monitors are mainly studied. The result shows that lateral edges of the model lead to a large number of separated vortices when the aircraft flies under large angle of attack, which cause strong interference with the vertical tail rudder. The interfered tail rudder exhibits obvious nonlinear and unsteady aerodynamic properties. In addition, the presence of separation vortices also leads to a significant increase in pressure fluctuation on the aircraft wall, especially on the leading edge of tail rudders. The power spectrum density of pressure shows that low frequency and high amplitude fluctuation of 200-300 Hz may cause structural damage.

Key words: unsteady, separation flow, pressure fluctuation, delayed detached-eddy simulation (DDES), numerical simulation

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发