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基于翼型Reynolds相似和等离子体射流相似准则,可在地面等效模拟位于平流层的等离子体流动控制效果。首先通过表面介质阻挡放电(SDBD)实验确定地面和平流层激励器的几何参数和放电参数,使等离子体射流具有相同的Reynolds数;然后采用几何、放电参数已知的激励器来控制翼型在地面和平流层飞行时(Reynolds数相同)的流动分离;最后采用数值模拟得到地面和平流层等离子体放电前后的翼型升力系数。结果表明:在施加流动控制后,翼型在地面条件飞行时的升力系数增幅与平流层基本一致。模拟平流层的准确度与翼型攻角有关,在临界攻角处偏差相对较大,其余攻角处偏差很小。在施加等离子体流动控制后,翼型在地面条件飞行的升力系数与平流层的升力系数在临界攻角处的偏差率在1.27%~5.26%之间;其余攻角处较小,在0.04%~0.98%之间。
Based on similar Reynolds-like and plasma jet-like criteria, surface-equivalent plasma flow control effects can be modeled in the stratosphere. Firstly, the geometrical and discharge parameters of the surface and stratospheric actuators are determined by SDBD experiments, so that the plasma jet has the same Reynolds number. Then, the geometry and parameters of the known discharge parameters are used to control the airfoil at Ground and stratosphere (Reynolds number same) flow separation; and finally numerical simulation of ground and stratospheric plasma discharge before and after the lift coefficient of the airfoil. The results show that after the flow control is applied, the lift coefficient of airfoil during ground flight is basically the same as that of the stratosphere. The accuracy of the simulated stratosphere is related to the angle of attack of the airfoil. The deviation at the critical angle of attack is relatively large, with little deviation at other angles of attack. After the plasma flow control was applied, the deviation rate of the lift coefficient of the airfoil on the ground flight and the stratospheric lift coefficient at the critical angle of attack was between 1.27% and 5.26% ~ 0.98% between.