This paper presents an investigation on the compressible flow past spanwise wavy wings with an incoming flow of $M_{\mathrm{\infty }}=0.5$ and $Re={10}^7$. The scale adaptive simulation is employed here to solve the Favre-averaged equations. Three wings, with the ratio of wavelengths (λ) to chord length (c) respectively equaling to 1/2 (W4), 1/3 (W6), 1/4 (W8), are aerodynamically investigated. The aerodynamic force and separation were compared. The results obtained show that the lift-to-drag ratio of W-8 is 12.7% and 14.4% higher than W-4 and W-6 because of the larger low-pressure regions, while the lift and drag coefficient curves of W-8 oscillate more strongly. Leading edge separated bubbles and dilation-type recirculation regions are observed in the flow field structures. Spanwise momentum transportation and local airflow downwash effect are generated by the flow around the separation regions. Spanwise momentum transportation and downwash effect play important roles in the flow control mechanism of spanwise wavy wings. Three components of three-dimensional velocity vectors are modally decomposed by dynamic mode decomposition method to reveal the flow control mechanisms and vortex structures. The main modes characterizing the motions of arched vortices and shear layer vortices have been obtained. Strouhal number (St) is adopted to define the periodic oscillations of vortex shedding. The St of the modes are related to the scale of the vortex structures in the flow field. Small-scale eddy motions have been decomposed in high-frequency modes, and thus the modes of the flow field are more meticulous for higher St.

本文介绍了通过展向波浪翼的可压缩流的研究，其中流入流为${米}_{\mathrm{\infty }}=0.5$和$Re={10}^7$. 这里采用尺度自适应模拟来求解 Favre 平均方程。三翼，波长 ( λ ) 与弦长 ( c ) 之比) 分别等于 1/2 (W4)、1/3 (W6)、1/4 (W8)，进行空气动力学研究。比较了气动力和分离度。所得结果表明，由于低压区较大，W-8的升阻比比W-4和W-6分别高出12.7%和14.4%，而W-的升阻系数曲线8 振荡更强烈。在流场结构中观察到前缘分离的气泡和膨胀型再循环区域。分离区域周围的流动产生了展向动量传输和局部气流下洗效应。展向动量传递和下洗效应在展向波浪翼的流动控制机制中起着重要作用。采用动态模态分解法对三维速度矢量的三个分量进行模态分解，揭示流动控制机制和涡流结构。获得了表征拱形涡和剪切层涡运动的主要模态。斯特鲁哈尔数 (采用St ) 来定义涡旋脱落的周期性振荡。模态的St与流场中涡结构的尺度有关。小尺度涡流运动在高频模式下被分解，因此流场模式对更高的St更细致。