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乘波体压缩面变化对其气动性能影响分析

崔凯 徐应洲 肖尧 李广利

崔凯, 徐应洲, 肖尧, 李广利. 乘波体压缩面变化对其气动性能影响分析[J]. 力学学报, 2017, 49(1): 75-83. doi: 10.6052/0459-1879-16-041
引用本文: 崔凯, 徐应洲, 肖尧, 李广利. 乘波体压缩面变化对其气动性能影响分析[J]. 力学学报, 2017, 49(1): 75-83. doi: 10.6052/0459-1879-16-041
Cui Kai, Xu Yingzhou, Xiao Yao, Li Guangli. EFFECT OF COMPRESSION SURFACE DEFORMATION ON AERODYNAMIC PERFORMANCES OF WAVERIDERS[J]. Chinese Journal of Theoretical and Applied Mechanics, 2017, 49(1): 75-83. doi: 10.6052/0459-1879-16-041
Citation: Cui Kai, Xu Yingzhou, Xiao Yao, Li Guangli. EFFECT OF COMPRESSION SURFACE DEFORMATION ON AERODYNAMIC PERFORMANCES OF WAVERIDERS[J]. Chinese Journal of Theoretical and Applied Mechanics, 2017, 49(1): 75-83. doi: 10.6052/0459-1879-16-041

乘波体压缩面变化对其气动性能影响分析

doi: 10.6052/0459-1879-16-041
基金项目: 

国家自然科学基金资助项目 11372324, 11572333

详细信息
    通讯作者:

    崔凯,副研究员,主要研究方向:飞行器构型设计和优化.E-mail:kcui@imech.ac.cn

  • 中图分类号: O354.4;V211.24

EFFECT OF COMPRESSION SURFACE DEFORMATION ON AERODYNAMIC PERFORMANCES OF WAVERIDERS

  • 摘要: 乘波体是一种利用激波包裹特性获得高升阻比的高速飞行器构型.已有研究中,乘波体气动性能的改善主要依赖于给定源流场条件下的前缘型线优化.本文采用数值优化和计算流体力学模拟为主要手段分析了乘波体压缩面变化对其气动性能的影响,以期有效拓展乘波体的设计空间.主要内容如下:首先给出了一种基于表面局部变形的乘波体设计方法.其次结合运用增量修正参数化方法、计算流体力学分析和微分演化算法构造了乘波体压缩面外形气动优化设计流程,以一种椭圆锥形流场生成的乘波体作为基准构型开展了无黏优化.之后从优化结果中选择升阻比递增的6个典型构型进行前缘钝化处理后,基于N-S方程对其气动性能进行了评估.最后综合依据无黏/黏性计算结果分析了乘波体压缩面变化对其气动性能的影响.结果表明该部分形状的改变对乘波体气动性能影响十分明显,在升力面积不变的条件下,乘波体压缩面形状变化可导致其升阻比出现成倍变化,即使在升力不减条件下,升阻比较基准构型也可获得超过14%的提升.此外,还可导致乘波体相对压心系数出现明显偏移.

     

  • 图  1  乘波体设计流程图示

    Figure  1.  Sketch of waverider construction

    图  2  具有相同激波面的源几何体

    Figure  2.  Generating bodies with the same shock layer

    图  3  外形参数化实例

    Figure  3.  An example of shape parameterization

    图  4  基准乘波体(半模)及其截面压力分布

    Figure  4.  Baseline waverider (half model) and its pressure contours at different cross section

    图  5  基准乘波体升阻比随攻角变化曲线

    Figure  5.  Variation of the lift-to-drag ratio values with flight angle of attack for baseline waverider

    图  6  微分演化算法流程图

    Figure  6.  Flowchart of differential evolution algorithm

    图  7  升阻比(a)和升力系数(b)收敛图

    Figure  7.  Convergence history of the $L/D$ (a) and the lift coefficient (b)

    图  8  两种乘波体的不同截面压力云图

    Figure  8.  Pressure contours at different cross-sections of the two waveriders

    图  9  乘波体尾缘压力等值线比较

    Figure  9.  Pressure contours comparison at the ending edge

    图  10  典型构型外形图

    Figure  10.  Geometries of typical waverider configurations

    图  11  钝化前缘乘波体黏性分析计算网格示意图

    Figure  11.  Grid structure for viscous analysis of blunt-edge waveriders

    图  12  不同乘波体尾缘压力分布云图比较

    Figure  12.  Pressure contours comparison at trailing edge plane of \different waveriders

    图  13  不同压缩面乘波体压力分布比较

    Figure  13.  Pressure contours on lower surfaces of waveriders with different compression surfaces

    表  1  设计变量的上下边界

    Table  1.   Boundary values of design space

    表  2  两种边界构型的设计变量和气动参数值

    Table  2.   Values of design variables and aerodynamic parameters of the two configurations

    表  3  典型构型黏性/无黏气动参数比较

    Table  3.   Comparison of aerodynamic parameters based on different numerical models for typical waveriders

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出版历程
  • 收稿日期:  2016-02-01
  • 修回日期:  2016-10-11
  • 网络出版日期:  2016-10-31
  • 刊出日期:  2017-01-18

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