Unsteady Wave Phenomena on a Supercritical Airfoil
Unsteady Wave Phenomena on a Supercritical Airfoil
复制标题
超临界翼型上的非定常波现象
DOI：
--
复制
发表时间：
2008
期刊：
影响因子：
--
通讯作者：
H. Olivier
中科院分区：
文献类型：
--
作者：
A. Alshabu;H. Olivier
跨音速流动研究是在带有矩形测试部分的改进激波管中进行的。所研究的模型是具有恒定弦长和锋利后缘的 BAC3-11 翼型。时间分辨阴影图和纹影图显示压力波在后缘附近发起并向上游传播，在前缘附近压力波明显变弱。这些波过程伴随着边界层中的尾流波动和涡旋的产生。观察到的波也由安装在翼型模型中的压力传感器捕获。主频率范围约为 0.7 至 1.5 kHz。通过对压力历史的统计分析，可以确定波传播方向和波速。对于较高的流动马赫数，还观察到强烈的波/冲击相互作用，其中根据冲击强度，冲击被衰减并退化为压缩波。
Transonic flow investigations are performed in a modified shock tube with a rectangular test section. The investigated model is a BAC3-11 airfoil with a constant cord length and a sharp trailing edge. Time-resolved shadowgraphs and schlieren pictures show pressure waves initiated near the trailing edge and propagating upstream, where they become apparently weaker near the leading edge. These wave processes are accompanied by wake fluctuations and vortex generation in the boundary layer. The observed waves are also captured by pressure transducers mounted in the airfoil model. The dominant frequencies range between approximately 0.7 and 1.5 kHz. Using statistical analysis of the pressure histories, wave propagation direction and wave speed are determined. For higher flow Mach numbers, a strong wave/shock interaction is also observed in which the shock, depending on the shock strength, is attenuated and degenerated into compression waves.