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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

余华峰, 刘宏康, 陈树生, 等 . 类X-51A飞行器非定常湍流精细模拟[J]. 北京航空航天大学学报, 2019, 45(3): 624-632. doi: 10.13700/j.bh.1001-5965.2018.0409
引用本文: 余华峰, 刘宏康, 陈树生, 等 . 类X-51A飞行器非定常湍流精细模拟[J]. 北京航空航天大学学报, 2019, 45(3): 624-632. doi: 10.13700/j.bh.1001-5965.2018.0409
YU Huafeng, LIU Hongkang, CHEN Shusheng, et al. High-resolution unsteady turbulence simulation of an X-51A-like aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(3): 624-632. doi: 10.13700/j.bh.1001-5965.2018.0409(in Chinese)
Citation: YU Huafeng, LIU Hongkang, CHEN Shusheng, et al. High-resolution unsteady turbulence simulation of an X-51A-like aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(3): 624-632. doi: 10.13700/j.bh.1001-5965.2018.0409(in Chinese)

类X-51A飞行器非定常湍流精细模拟

doi: 10.13700/j.bh.1001-5965.2018.0409
基金项目: 

国家自然科学基金 11721202

详细信息
    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

    通讯作者:

    阎超, E-mail:05642@buaa.edu.cn

  • 中图分类号: V221+.3

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

Funds: 

National Natural Science Foundation of China 11721202

More Information
  • 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。

     

  • 图 1  计算网格

    Figure 1.  Computational grid

    图 2  瞬时密度梯度云图

    Figure 2.  Instantaneous density gradient contour

    图 3  剪切层速度型

    Figure 3.  Velocity profiles in shear layer

    图 4  沿斜坡的时均压力和压力脉动均方根

    Figure 4.  Mean and root mean square of pressure fluctuation along ramp

    图 5  计算模型

    Figure 5.  Computational model

    图 6  飞行器计算网格

    Figure 6.  Computational grids of vehicle

    图 7  壁面计算网格

    Figure 7.  Wall surface computational grid

    图 8  瞬态流场结构(Q=200/s2)

    Figure 8.  Structure of transient flow field (Q=200/s2)

    图 9  瞬时密度梯度截面

    Figure 9.  Instantaneous density gradient slices

    图 10  尾舵升、侧力系数随迎角变化

    Figure 10.  Variation of lift and side force coefficient of tail rudder with angle of attack

    图 11  升力系数脉动曲线

    Figure 11.  Lift coefficient fluctuation curves

    图 12  整机压力系数脉动均方根云图

    Figure 12.  Contours of root mean square of pressure coefficient fluctuation for complete vehicle

    图 13  尾舵压力系数脉动均方根云图

    Figure 13.  Contours of root mean square of pressure coefficient fluctuation for tail rudders

    图 14  “V”型尾舵监测点

    Figure 14.  Monitoring points on "V" shape tail rudder

    图 15  “V”型尾舵不同高度瞬时密度梯度截面

    Figure 15.  Instantaneous density gradient slices of "V" shape tail rudder at different height

    图 16  不同位置功率谱密度对比

    Figure 16.  Comparison of power spectrum density at different locations

    图 17  四个不同时刻Q等值面(Q=400/s2)

    Figure 17.  Iso-surface of Q-criterion at four different moments(Q=400/s2)

    图 18  四个不同时刻压缩面附近对称面马赫数云图

    Figure 18.  Ma contours of symmetry plane near compressed surface at four different moments

    表  1  计算状态

    Table  1.   Computational condition

    参数 马赫数 来流静压/Pa 来流静温/K 来流单位雷诺数/m-1
    数值 2.92 31 415 145 4.5×107
    下载: 导出CSV
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出版历程
  • 收稿日期:  2018-07-09
  • 录用日期:  2018-07-27
  • 刊出日期:  2019-03-20

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