| Citation: | GUO Chongjia, YANG Xudong, HAN Ji’ang, et al. Flow control technology for diffuser cascades inspired by dragonfly wing corrugation structures[J]. Journal of Aerospace Power, 2026, 41（X）：20250584 doi: 10.13224/j.cnki.jasp.20250584
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Inspired by the flow-control capability of corrugated structures on dragonfly wings, a streamwise-arranged non-smooth surface was proposed and applied to a highly loaded diffuser cascade. Using a numerically validated simulation approach, the effects of groove location and structural parameters on the aerodynamic performance of the cascade were systematically investigated, and the underlying mechanisms were elucidated from both macroscopic flow features and near-wall flow physics. The results indicated that when the grooves were arranged within 75%—100% of axial chord length on the suction surface with an appropriate parameter combination, stable trapped vortices were formed inside the groove cavities. Through periodic interaction with the main flow, these trapped vortices introduced small-scale, amplitude-limited disturbances in the near-wall region, leading to an increase in the turbulence intermittency factor without triggering high-energy large-scale turbulent structures. Meanwhile, the local retention and redistribution of reversed-flow momentum promoted a transition of the separated region from a highly unstable, high-energy state to a more moderate and controlled turbulent state. Consequently, the separation vortex near the trailing edge on the suction side was significantly weakened, passage blockage was alleviated, and the development of the suction-side boundary layer was effectively improved. Based on the double design point loss criterion, the total pressure loss was reduced by up to 8.66% within the usable incidence angle range, and the upper boundary of the usable incidence angle was extended by approximately 0.7° toward higher values.
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