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Effect of Wall Blowing on Hypersonic Boundary-Layer Transition

机译：吹壁对高超音速边界层过渡的影响

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An investigation of outgassing effects on boundary-layer transition was carried out. This joint computationalexperimental work mimicked heat-shield pyrolysis outgassing in atmospheric reentry conditions. A slender 7 deg half-angle cone with air wall blowing through a porous section near the apex was tested in the VKI-H3 Mach 6 hypersonic blowdown noisy wind tunnel. The steady transition onset location was measured using infrared thermography, whereas gaseous-naphthalene-based planar laser-induced fluorescence imaging enabled the visualization and quantification of the spatial characteristics of the instabilities. Linear stability theory, combined with the semiempirical eN method with N = 5.9, was used to predict the location of transition onset in the same configurations. Studies were performed at different freestream unit Reynolds numbers and blowing rates. Numerical and experimental results agreed within the experimental uncertainties, and they coincided with the previously reported advancement of the transition location due to wall blowing. The wave numbers of the most amplified secondmode instabilities obtained with the linear stability theory matched the observations done with planar laser-induced fluorescence, suggesting it was the growth of such perturbations that led to the transitioning of the boundary layer. The porous section was seen to destabilize the boundary layer for nonblowing configurations. Regarding the upstream advancement of transition associated with wall blowing, the numerical analysis suggested that it is a consequence of the increase in the range of unstable frequencies in the wall-blowing region. Blowing nonuniformities in the cone's longitudinal direction were observed to have no influence on the local transition location under noisy conditions.
机译：研究了除气对边界层过渡的影响。这项联合计算实验工作模仿了大气再入条件下的热屏蔽热解出气。在VKI-H3 Mach 6高超声速排污嘈杂的风洞中测试了细长的7度半角圆锥体，其空气壁吹过顶点附近的多孔部分。使用红外热像仪测量了稳定转变的起始位置，而基于气态萘的平面激光诱导的荧光成像则可以对不稳定性的空间特征进行可视化和量化。线性稳定性理论与N = 5.9的半经验eN方法相结合，被用来预测相同构型下过渡转变的位置。研究在不同的自由流单位雷诺数和吹气速率下进行。数值和实验结果在实验不确定性范围内是一致的，并且与先前报道的由于吹墙而引起的过渡位置的进展相吻合。通过线性稳定性理论获得的最大放大的第二模态不稳定性的波数与对平面激光诱导的荧光的观察结果相符，表明正是这种扰动的增长导致了边界层的转变。对于非发泡构造，可以看到多孔部分使边界层不稳定。关于与壁吹相关的过渡的上游进展，数值分析表明，这是壁吹区域中不稳定频率范围增加的结果。在嘈杂条件下，观察到圆锥体纵向吹胀不均匀对局部过渡位置没有影响。

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  • 来源
    《AIAA Journal》 |2019年第4期|1567-1578|共12页
  • 作者

    Miro Fernando Miro; Dehairs Pieter; Pinna Fabio; Gkolia Maria; Masutti Davide; Reger Tamas; Chazot Olivier;

  • 作者单位

    von Karman Inst Fluid Dynam, Aeronaut & Aerosp Dept, Chaussee Waterloo 72, B-1640 Rhode St Genese, Belgium;

    von Karman Inst Fluid Dynam, Aeronaut & Aerosp Dept, Chaussee Waterloo 72, B-1640 Rhode St Genese, Belgium;

    von Karman Inst Fluid Dynam, Aeronaut & Aerosp Dept, Chaussee Waterloo 72, B-1640 Rhode St Genese, Belgium;

    von Karman Inst Fluid Dynam, Aeronaut & Aerosp Dept, Chaussee Waterloo 72, B-1640 Rhode St Genese, Belgium;

    von Karman Inst Fluid Dynam, Aeronaut & Aerosp Dept, Chaussee Waterloo 72, B-1640 Rhode St Genese, Belgium;

    von Karman Inst Fluid Dynam, Aeronaut & Aerosp Dept, Chaussee Waterloo 72, B-1640 Rhode St Genese, Belgium;

    von Karman Inst Fluid Dynam, Aeronaut & Aerosp Dept, Chaussee Waterloo 72, B-1640 Rhode St Genese, Belgium;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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