Experimental Investigation of Buffet Onset and Penetration on a Supercritical Airfoil at Transonic Speeds
Experimental Investigation of Buffet Onset and Penetration on a Supercritical Airfoil at Transonic Speeds
复制标题
跨音速超临界翼型的抖振爆发和侵彻实验研究
DOI：
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发表时间：
1990
期刊：
影响因子：
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通讯作者：
D. Basler
中科院分区：
文献类型：
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作者：
E. Stanewsky;D. Basler
摘要对超临界翼型CAST 7/DOA1进行了试验研究，确定了马赫数、迎角和雷诺数等参数对颤振过程，特别是对激波振荡频率和幅值的影响。在本研究中，该模型配备了规则压力孔、动态压力传感器和热膜传感器，后者用于确定过渡位置和分离区域。采用全息高速实时干涉仪对流场进行观测。分析结果表明，上表面激波与边界层的相互作用驱动了颤振过程，特别是影响了激波分离泡的发展，并导致翼型后缘流动条件的变化，在强颤振区域内，激波振荡频率随雷诺数的增加而减小，振幅随雷诺数的增加而增大。
Abstract : An experimental investigation was carried out on the supercritical airfoil CAST 7/DOA1 to determine the influence of three parameters--Mach number, angle of attack and most of all Reynolds number--on the buffet process and especially on the shock oscillation frequency and amplitude. For this investigation, the model was equipped with regular pressure orifices, dynamic pressure transducers and hot-film sensors, the latter used to determine transition location and regions of separation. The flow field was observed by a holographic high-speed, real-time interferometer. Analysis of the results revealed that the buffet process is essentially driven by the interaction of the upper surface shock wave with the boundary layer, especially as it influences the development of the shock-induced separation bubble, and the resultant change in flow conditions at the airfoil trailing edge and that, within the domain of intensive buffet, the shock oscillation frequency decreases with Reynolds number while the amplitude increases.