Experiment of the plasma active flow control based on pressure feedback
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摘要:
基于翼面压力分布与流动分离的对应关系，提出了一种用于等离子体激励抑制翼面流动分离的反馈控制方法，该方法通过模型表面特征点的压力判断流动分离情况，根据判断结果自动施加或取消等离子体控制。在NACA0015翼型和飞翼布局模型上分别对该方法进行了风洞试验验证，试验表明：基于压力反馈的等离子体流动控制方法能够实现对翼面流动分离的主动控制，通过控制能够改善模型的失速特性；在飞翼布局模型上，等离子体压力反馈控制与开环控制的效果基本一致，在来流风速为30 m/s时反馈控制与开环控制均能使模型的最大升力系数提高27%以上、失速迎角推迟4°。
Abstract:Based on the corresponding relationship between the wing pressure distribution and flow separation, a feedback control method for separation flow control by plasma was proposed. Using this method, the separation of wing surface can be distinguished by the pressure of the characteristic points on the model surface, and the plasma flow control can be automatically applied or canceled according to the judgment results. The method was verified on NACA0015 airfoil and flying wing layout models respectively in wind tunnel experiment. The experiment showed that the plasma flow control method based on pressure feedback can realize the automatic suppression of the wing flow separation, thus improving the stall characteristics of the model. The effect of the plasma based on pressure feedback was consistent with that of open-loop control. Both of them can increase the maximum lift coefficient of the flying wing layout model by more than 27% and the stall angle of attack by 4° at a wind speed of 30 m/s.
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Key words:
- flow control /
- plasma /
- flow separation /
- feedback control /
- wind tunnel experiment
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图 1 测压孔在翼型上的分布（单位：mm）
Figure 1. Distribution of piezometric holes on airfoils （unit：mm）
图 4 V=20 m/s 时NACA0015翼型表面压力分布
Figure 4. Surface pressure distribution curve of NACA0015 airfoil at V=20 m/s
图 5 V=30 m/s时NACA0015翼型表面压力分布曲线
Figure 5. Surface pressure distribution curve of NACA0015 airfoil at V=30 m/s
图 9 V=20 m/s特征点压力系数和等离子体激励电压随迎角增大的历程曲线
Figure 9. History cure of pressure coefficient of characteristic point and excitation voltage of plasma with the increase of angle of attack at V=20 m/s
图 10 V=20 m/s特征点压力系数和等离子激励电压随迎角减小的历程曲线
Figure 10. History cure of pressure coefficient of characteristic point and excitation voltage of plasma with the decrease of angle of attack at V=20 m/s
图 11 V=20 m/s，NACA0015翼型等离子体闭环流动控制测压曲线
Figure 11. Surface pressure distribution curve of NACA0015 airfoil with plasma closed-loop flow control at V=20 m/s
图 12 飞翼模型上的等离子体闭环流动控制特征点
Figure 12. Characteristic point of plasma closed-loop flow control on the flying wing model
图 13 V=30 m/s时飞翼模型等离子体压力反馈控制和开环控制试验曲线
Figure 13. Experiment curves of closed-loop flow control and open-loop flow control of plasma on flying-wing model at V=30 m/s
表 1 天平量程和相对误差
Table 1. Measurement range and relative error of the balance
测量单元 天平量程 相对误差/% 升力 ±300 N 0.09 阻力 ±150 N 0.22 侧力 ±100 N 0.30 偏航力矩 ±12 N·m 0.29 滚转力矩 ±10 N·m 0.14 俯仰力矩 ±12 N·m 0.11 
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