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下表面射流的超临界翼型气动性能分析

王若尘 张国鑫 王翔宇 马晓平

王若尘,张国鑫,王翔宇,等. 下表面射流的超临界翼型气动性能分析[J]. 北京航空航天大学学报,2023,49(7):1671-1679 doi: 10.13700/j.bh.1001-5965.2021.0489
引用本文: 王若尘,张国鑫,王翔宇,等. 下表面射流的超临界翼型气动性能分析[J]. 北京航空航天大学学报,2023,49(7):1671-1679 doi: 10.13700/j.bh.1001-5965.2021.0489
WANG R C,ZHANG G X,WANG X Y,et al. Aerodynamic performance analysis of supercritical airfoil with lower surface jet[J]. Journal of Beijing University of Aeronautics and Astronautics,2023,49(7):1671-1679 (in Chinese) doi: 10.13700/j.bh.1001-5965.2021.0489
Citation: WANG R C,ZHANG G X,WANG X Y,et al. Aerodynamic performance analysis of supercritical airfoil with lower surface jet[J]. Journal of Beijing University of Aeronautics and Astronautics,2023,49(7):1671-1679 (in Chinese) doi: 10.13700/j.bh.1001-5965.2021.0489

下表面射流的超临界翼型气动性能分析

doi: 10.13700/j.bh.1001-5965.2021.0489
基金项目: 国家自然科学基金(61901448); 中国科学院青年创新促进会(2020149)
详细信息
    通讯作者:

    E-mail:zhangguoxin@iet.cn

  • 中图分类号: V211.3

Aerodynamic performance analysis of supercritical airfoil with lower surface jet

Funds: National Natural Science Foundation of China (61901448); Youth Innovation Promotion Association of Chinese Academy of Sciences (2020149)
More Information
  • 摘要:

    为探究下表面射流关键参数对超临界翼型气动性能的影响,采用雷诺平均Navier-Stokes (RANS)方程与Spalart-Allmaras (S-A)湍流模型进行数值模拟。通过比较基准RAE2822翼型与下表面射流翼型的流场,验证下表面射流能够在翼型后缘诱导产生逆时针分离涡,带动流线向下偏折,增加了翼型的等效弯度,同时加大前缘的吸力峰,从而提高翼型的气动性能。进一步探究射流位置、射流动量系数、射流角度、马赫数等关键参数对RAE2822翼型气动性能的影响规律。结果表明:给定状态下,下表面射流的位置越靠后,动量系数越大,翼型的气动性能越优。下表面射流在α=0°和2°时的最优射流角度为110°,在α=4°时的最优射流角度为160°,且在最优射流角度下能有效提高翼型马赫数在0.3~0.6范围内的气动性能。

     

  • 图 1  RAE2822翼型下表面射流参数示意图

    Figure 1.  Diagram of jet parameters of RAE2822 airfoil lower surface

    图 2  RAE2822翼型计算网格

    Figure 2.  Computational grids of RAE2822 airfoil

    图 3  RAE2822压力系数分布对比

    Figure 3.  Comparison of pressure coefficient distribution of RAE2822

    图 4  CC020-010EJ翼型计算网格

    Figure 4.  Computational grids of CC020-010EJ airfoil

    图 5  CC020-010EJ压力系数分布对比

    Figure 5.  Comparison of pressure coefficient distribution of CC020-010EJ

    图 6  RAE2822下表面射流翼型计算网格

    Figure 6.  Computational grids of jet airfoil of RAE2822 lower surface

    图 7  马赫云图与流线图对比

    Figure 7.  Comparison of Mach contours and streamlines

    图 8  有/无射流压力系数分布对比

    Figure 8.  Comparison of pressure coefficient distribution with/without jet

    图 9  不同射流位置气动力系数对比

    Figure 9.  Comparison of aerodynamic coefficients at different jet positions

    图 10  不同射流位置马赫云图与流线图对比

    Figure 10.  Comparison of Mach contours and streamlines at different jet positions

    图 11  不同射流动量系数下气动力系数对比图

    Figure 11.  Comparison of aerodynamic coefficients at different jet momentum coefficients

    图 12  不同射流角度下各个气动力系数对比

    Figure 12.  Comparison of aerodynamic coefficients at different jet angles

    图 13  不同马赫数下各个气动力系数对比

    Figure 13.  Comparison of aerodynamic coefficients at different Mach numbers

    表  1  RAE2822翼型网格参数与气动力系数的对比

    Table  1.   Comparison of grid parameters and aerodynamic coefficients of RAE2822 airfoil

    网格网格数量CLCD
    实验值[21]0.8030.0168
    粗网格233240.760310.016989
    中等网格409640.766520.017031
    细网格691880.769280.017094
     注:3套网格与实验值相比,CL误差5.3%,4.5%,4.2%,CD误差为1.1%,1.3%,1.8%。
    下载: 导出CSV

    表  2  CC020-010EJ翼型气动力系数的对比

    Table  2.   Comparison of aerodynamic coefficients of CC020-010EJ airfoil

    结果CLCD
    计算值1.5430.0348
    文献[22]数值结果1.5330.0367
    实验值[22]1.3630.0312
     注:本文,文献[22]计算值与实验值相比,CL误差为13.2%,12.4%,CD误差为11.5%,17.6%。
    下载: 导出CSV

    表  3  下表面射流计算参数

    Table  3.   Computational parameters of lower surface jet

    Ma Re α/(°) cμ xj θ/(°)
    0.6 5.35×106 4 0.005 0.98c 90
    下载: 导出CSV

    表  4  不同射流位置下的计算参数

    Table  4.   Computational parameters of different jet positions

    Ma Re α/(°) cμ xj θ/(°)
    0.6 5.35×106 −4~16 0.005 0.8c,0.9c,0.98c 90
    下载: 导出CSV

    表  5  不同射流动量系数下的计算参数

    Table  5.   Computational parameters of different jet momentum coefficients

    Ma Re α/(°) cμ xj θ/(°)
    0.6 5.35×106 −4~16 0.0005,0.001,0.005 0.98c 90
    下载: 导出CSV

    表  6  4°迎角下不同射流动量系数翼型的气动力系数

    Table  6.   Aerodynamic coefficients of airfoil with different jet momentum coefficients at angle of attack 4°

    cμCLCDCL /CD
    00.779820.01309559.55
    0.00050.930050.01412165.86
    0.0010.980810.01436668.27
    0.0051.17010.01533776.29
    下载: 导出CSV

    表  7  不同射流角度计算参数

    Table  7.   Computational parameters of different jet angles

    Ma Re α/(°) cμ xj θ/(°)
    0.6 5.35×106 0,2,4 0.005 0.98c 10~170
    下载: 导出CSV

    表  8  不同马赫数下的计算参数

    Table  8.   Computational parameters of different Mach numbers

    Ma Re α/(°) cμ xj θ/(°)
    0.3~0.6 2.68×106~5.35×106 0、2、4 0.005 0.98c 110,160
    下载: 导出CSV
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出版历程
  • 收稿日期:  2021-08-25
  • 录用日期:  2021-09-10
  • 网络出版日期:  2021-09-24
  • 整期出版日期:  2023-07-31

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