Experimental/Numerical Investigation Airfoil with Flow Control by Synthetic Jets (CD) (paper ICAS 2012-3.7.5)
Experimental/Numerical Investigation Airfoil with Flow Control by Synthetic Jets (CD) (paper ICAS 2012-3.7.5)
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通过合成射流控制流量的实验/数值研究翼型 (CD)（论文 ICAS 2012-3.7.5）
DOI：
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发表时间：
2012
期刊：
影响因子：
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通讯作者：
I. Grant
中科院分区：
文献类型：
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作者：
Stephanus Widjanarko;I.J.A.K. Geesing;D. Vries;H. Hoeijmakers;I. Grant
本文研究了机翼气动载荷主动控制问题。对于负载控制，需要在大迎角范围内调节气动特性。这可以通过引入合成射流来调节翼型的环量来实现，该合成射流的出口垂直于后缘附近位置处的表面。数值和实验研究的机翼是一个非后掠二元机翼，NACA 0018剖面，展向缝x/c = 0.88。为了消除在本研究中考虑的雷诺数（Re = 88，000 − 550，000）下出现的层流分离气泡，采用了不同的冷却带。所得到的测量压力分布已被解释的帮助下，从XFOIL的结果。总的来说，结果显示出令人满意的一致性。对α = 0 °和α = 8 °的情况进行了合成射流流动控制的参数研究，在Re = 165，000 cl/cd时最大。该研究是在低频区域进行的，即无量纲频率F + = O（1）。流动控制的有效性进行了研究，为不同的频率和出流速度。对于目前的配置，最明显的效果是在低致动频率和高射流强度。合成射流激励的有效性在很宽的攻角范围内观察到最小的阻力惩罚。测量的Cp分布进行了比较与数值模拟的Cp分布。数值模拟揭示了驱动在修改后缘流的细节，从而洞察合成射流的诱导效应。总的来说，射流效率是射流强度、驱动频率和攻角的函数
The paper deals with the investigation of active aero-fluidic load control for wings. For load control, it is required to adjust the aerodynamic characteristics over a wide range of angles of attack. This can be achieved by adjusting the circulation of the airfoil by introducing synthetic jets with the exit normal to the surface at a location near the trailing edge. The wing investigated numerically and experimentally is an unswept, two-dimensional wing with a NACA0018 section with spanwise slits at x/c = 0.88. Different turbulator tapes have been employed in order to remove the laminar separation bubble which appears for the Reynolds number considered in the present study (Re = 88,000 − 550,000). The resulting measured pressure distributions have been interpreted with the help of results from XFOIL. In general, the results have shown a satisfactory agreement. A parametric study with flow control by synthetic jets has been carried out for α = 0 and for α = 8 deg., for which at Re = 165,000 cl/cd is maximal. The study has been performed in the low-frequency regime, i.e. the dimensionless frequency F + = O(1). The effectiveness of flow control is investigated for different frequencies and outflow velocities. For the current configuration, the most distinct effect is at low actuation frequency and at high jet strength. The effectiveness of the synthetic jet actuation is observed in a wide range of angles of attack with a minimum drag penalty. Measured Cp distributions have been compared with numerically simulated Cp distributions. The numerical simulation reveals details of the actuation in modifying the trailing edge flow giving insight in the induced effect by synthetic jets. Overall, the jet effectiveness is a function the jet strength, actuation frequency and the angle of attack