PIV around a NACA0012 Airfoil with a Plasma Actuator for Noise Reduction
PIV around a NACA0012 Airfoil with a Plasma Actuator for Noise Reduction
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NACA0012 翼型周围的 PIV，带有用于降噪的等离子致动器
DOI：
10.2514/6.2010-1412
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发表时间：
2010
期刊：
影响因子：
--
通讯作者：
Motofumi Tanaka
中科院分区：
文献类型：
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作者：
S. Koike;K. Mitsuo;H. Kato;H. Ura;Shigeya Watanabe;Motofumi Tanaka
采用介质阻挡放电等离子体致动器（PA）来降低NACA 0012机翼模型的后缘噪声和涡流。长度为1 m的PA安装在模型压力侧弦长的60%处。采用2D-PIV测量了均匀流速为15、30和40 m/s时模型尾缘附近的速度场。三种情况下基于模型代码长度的雷诺数分别为2.0 × 10 5、4.0 × 10 5和5.4 × 10 5。当PA关闭时，测量的速度和适当的正交分解的结果表明，在15 m/s的均匀流速下，模型后缘周期性地发射出强涡。PA显著地减少了这些尾涡。随着均匀来流速度的增加，尾缘涡减小。结果表明，随着均匀流速的增加，PA的效果降低。
A dielectric barrier discharge plasma actuator (PA) was applied to reduce trailing edge noise and vortices emitted from a NACA0012 airfoil model. The PA in length of 1 m was installed at 60 % of the chord length on the pressure side of the model. The velocity field around the trailing edge of the model was measured via 2D-PIV at the uniform flow velocity of 15, 30, and 40 m/s. The Reynolds numbers based on the code length of the model for the three cases were 2.0x10 5 , 4.0x10 5 , and 5.4x10 5 , respectively. When the PA was off, the measured velocity and the result of the proper orthogonal decomposition showed that the strong vortices were periodically emitted from the trailing edge of the model at the uniform flow velocity of 15 m/s. These trailing vortices were dramatically reduced by the PA. As the uniform flow velocity increased, the trailing edge vortices decreased. As the result, the effect of the PA was decreased as the uniform flow velocity increased.