沙心国, 郭跃, 纪锋, 袁湘江, 沈清. 高超声速圆锥边界层失稳条纹结构实验研究[J]. 空气动力学学报, 2020, 38(1): 143-147. DOI: 10.7638/kqdlxxb-2019.0141
引用本文: 沙心国, 郭跃, 纪锋, 袁湘江, 沈清. 高超声速圆锥边界层失稳条纹结构实验研究[J]. 空气动力学学报, 2020, 38(1): 143-147. DOI: 10.7638/kqdlxxb-2019.0141
SHA Xinguo, GUO Yue, JI Feng, YUAN Xiangjiang, SHEN Qing. Experimental study on instability streak structure over a hypersonic cone[J]. ACTA AERODYNAMICA SINICA, 2020, 38(1): 143-147. DOI: 10.7638/kqdlxxb-2019.0141
Citation: SHA Xinguo, GUO Yue, JI Feng, YUAN Xiangjiang, SHEN Qing. Experimental study on instability streak structure over a hypersonic cone[J]. ACTA AERODYNAMICA SINICA, 2020, 38(1): 143-147. DOI: 10.7638/kqdlxxb-2019.0141

高超声速圆锥边界层失稳条纹结构实验研究

Experimental study on instability streak structure over a hypersonic cone

  • 摘要: 边界层转捩的准确预测是高超声速飞行面临的关键气动问题之一。为研究高超声速边界层失稳和转捩机理,以前缘半径1.6mm、半锥角7°的圆锥模型为研究对象,在FD-07高超声速风洞中采用红外热图技术开展边界层转捩实验测量。通过与工程计算结果对比,确认模型表面边界层流态。实验结果表明:有迎角条件下,模型表面中后段出现条纹结构,条纹结构的起始位置随着周向角的增加而向上游移动;随着迎角的增加,条纹起始位置向上游移动,条纹强度差异和条纹与模型中心线的夹角越来越大。实验获得的条纹结构与不同频率扰动波相互作用直接数值模拟获得的条纹结构现象一致。通过对比分析,认为边界层内不同频率扰动波相互作用是产生条纹结构的一种机制。

     

    Abstract: Boundary layer transition prediction is one of the key aerodynamic issues for hypersonic flight. In order to study the transition mechanism, a 7° half angle cone with nose radius of 1.6mm was experimented using infrared thermography (IR) in the hypersonic wind tunnel FD-07 at China Academy of Aerospace Aerodynamics. The heat flux obtained by IR was compared with that by the engineering method to confirm the boundary layer state on the model surface. The results show that streaks arise on the model surface at an angle of attack, the streaks starting position move upstream with circumferential angle increasing, and the attack angle have a big effect on the streaks distribution. Streaks obtained by the wind tunnel test present good agreement with the direct numerical simulation, it can conclude that the interaction of different frequency disturbances in the boundary layer is one of the mechanisms for generating the streaks.

     

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