合成双射流控制带冰脊翼型气动特性数值模拟研究

Numerical study on the aerodynamic performance of ice ridge airfoil with dual synthetic jets actuator

摘要:

机翼防/除冰过程中或过冷大水滴条件下形成的冰脊会严重破坏机翼的气动特性，影响飞行安全。为进一步提升带冰脊翼型的飞行性能，采用基于合成双射流的主动流动控制方法，通过数值仿真，开展基于合成双射流的 NACA0012 带冰脊翼型气动特性控制研究，探索合成双射流提升带冰脊翼型气动特性的效果和机理，以及合成双射流动量、频率、角度、位置等参数对控制效果的影响。结果表明：合成双射流提升带冰脊翼型气动性能的控制机理包括吸除、注入和掺混效应；在无量纲频率 F+=1，动量系数 Cμ=0.3 的约束下，合成双射流控制下能够使失速迎角提升 3°，α=10° 时升力系数提升 68.8%，阻力系数降低 46.7%；射流控制参数对控制效果有较大的影响，射流动量系数越大，控制效果越好；无量纲控制频率 F+=0.2 时取得最佳控制效果；射流角度在45°~75° 范围内均有较好的控制效果；射流出口位于 0.2 倍弦长处控制效果最佳。

Abstract:

The ice ridge formed during the anti/de-icing or under the condition of supercooled large droplet will seriously damage the aerodynamic performance of the airfoil and affect flight safety. In order to improve the flight performance of ice ridge airfoil, the active flow control method based on dual synthetic jet was adopted. The aerodynamic performance control of NACA0012 ice ridge airfoil based on dual synthetic jet was studied through numerical simulation. The effect and mechanism of dual synthetic jet on improving the aerodynamic performance of ice ridge airfoil, and the influence of parameters such as momentum, frequency, angle and position of dual synthetic jet were explored. The results show that adding dual synthetic jet at appropriate position on the wing surface can effectively improve the lift, reduce the drag and expand the stall angle of attack. The dual synthetic jet control parameters have a significant impact on the control effect. The larger the jet momentum coefficient, the better the control effect, the optimal control effect is achieved when the dimensionless control frequency is around 0.2, the jet angle has a good control effect within the range of 30°-75°, and the control effect is best when the jet outlet is located near 0.2 times the chord length.