Abstract
The hydrodynamic performance of the blended-wing-body underwater glider can be improved by opening a hole on the surface and applying the steady suction active flow control. In order to explore the influence law and mechanism of the steady suction active flow control on the lift and drag performance of the hydrofoil, which is the profile of the blended-wing-body underwater glider, based on the computational fluid dynamics (CFD) method and SST k-ω turbulence model, the steady suction active flow control of hydrofoil under different conditions is studied, which include three suction factors: suction angle, suction position and suction ratio, as well as three different flow states: no stall, critical stall and over stall. Then the influence mechanism in over stall flow state is further analyzed. The results show that the flow separation state of NACA0015 hydrofoil can be effectively restrained and the flow field distribution around it can be improved by a reasonable steady suction, so as to the lift-drag performance of NACA0015 hydrofoil is improved. The effect of increasing lift and reducing drag of steady suction is best at 90° suction angle and symmetrical about 90° suction angle, and it is better when the steady suction position is closer to the leading edge of the hydrofoil. In addition, with the increase of the suction ratio, the influence of steady suction on the lift coefficient and drag coefficient of hydrofoil is greater.
Highlights
The hydrodynamic performance of the blended⁃wing⁃body underwater glider can be improved by opening a hole on the surface and applying the steady suction active flow control
In order to explore the influence law and mechanism of the steady suction active flow control on the lift and drag performance of the hydrofoil,which is the profile of the blended⁃wing⁃body underwater glider, based on the computational fluid dynamics ( CFD) method and SST k⁃ω turbulence model, the steady suction active flow control of hydrofoil under different conditions is studied, which include three suction factors: suction angle, suction position and suction ratio, as well as three different flow states: no stall, critical stall and over stall
The results show that the flow separation state of NACA0015 hydrofoil can be effectively restrained and the flow field distribution around it can be improved by a reasonable steady suction, so as to the lift⁃drag performance of NACA0015 hydrofoil is improved
Summary
西北工业大学学报 Journal of Northwestern Polytechnical University https: / / doi.org / 10.1051 / jnwpu / 20213940801 性系数; - ρ u′i u′j 为雷诺应力项;Si 为广义源项。 1.2.2 SST k⁃ω 湍流模型 从图 3 中可知,NACA0015 翼型的升力系数仿 真值与实验值总体上吻合较好,说明本文基于 SST k⁃ω 湍流模型建立的水下滑翔机翼型流场数值计算 方法是可行的。
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