Analysis of transonic buffet on ONERA-M4 model with unsteady pressure-sensitive paint
Analysis of transonic buffet on ONERA-M4 model with unsteady pressure-sensitive paint
复制标题
非定常压敏涂料ONERA-M4模型跨音速抖振分析
DOI：
10.1007/s00348-021-03228-1
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发表时间：
2021
影响因子：
2.4
通讯作者：
Seiichi Sonoda
中科院分区：
文献类型：
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作者：
Kazuki Uchida;Yosuke Sugioka;Miku Kasai;Yuji Saito;Taku Nonomura;Keisuke Asai;Kazuyuki Nakakita;Yusuke Nishizaki;Yoshiyuki Shibata;Seiichi Sonoda
采用非定常压敏涂料（PSP）研究了ONERA-M4模型的跨音速振动。在马赫数为0.84、弦雷诺数为的吹落式跨声速风洞中进行了风洞试验。攻角在两者之间变化不定。左翼涂有低表面粗糙度的聚合物/陶瓷PSP，右翼涂有温度敏感涂料。对测量的PSP数据进行处理，计算时间序列压力系数、均方根压力系数波动、功率谱密度、相干性和相移。非定常压力场的行为与前人在NASA通用研究模型（CRM）中观察到的不同。随着攻角的增大，激波振荡的主导频率由低斯特劳哈尔数分量（）向凸斯特劳哈尔数分量（中心频率）转移。随着迎角的增大，两种模型的分离过程也有所不同。在CRM中，分离从跨中区域开始，而在ONERA-M4模型中，分离从翼尖开始。在ONERA-M4模型中未观察到称为“自助餐细胞”的特征压力波动。这些差异被认为是由模型几何形状的差异引起的，如机翼扭曲和翼型横截面轮廓。图形抽象
The transonic buffet on an ONERA-M4 model was experimentally investigated using an unsteady pressure-sensitive paint (PSP) in the present study. Wind tunnel tests were conducted in a blowdown-type transonic wind tunnel at a Mach number of 0.84 and a chord Reynolds number of. The angle of attack was varied in betweenand. The left wing was painted with a polymer/ceramic PSP with low surface roughness, and the right wing was painted with a temperature-sensitive paint. The measured PSP data were processed to calculate time-series pressure coefficients, root-mean-squares pressure-coefficient fluctuations, power spectral density, coherence, and phase shift. The behavior of the unsteady pressure field was different from that observed for the NASA Common Research Model (CRM) in a previous study. The dominant frequency of the shock oscillation shifted from the low-Strouhal-number component () to the bump Strouhal number (for the center frequency) with increasing angle of attack. The separation processes with an increasing angle of attack were also found to be different for the two models. The separation starts from the mid-span region in the CRM, while the separation starts from the wingtip in the ONERA-M4 model. The characteristic pressure fluctuations known as “buffet cells” were not observed for the ONERA-M4 model. These differences are considered to be caused by the difference in model geometries, such as the wing twist and the airfoil cross-sectional profile.Graphical abstract