高亚声速层流翼型转捩数值模拟及试验研究

Numerical simulation and test on transition of a high subsonic laminar airfoil

自然层流翼型可以显著减小机翼的摩擦阻力,是飞机减阻设计的重要手段之一。基于某高亚声速飞机的应用需求设计了一款层流翼型,采用γ-Reθ转捩模型开展了翼型绕流流场的数值模拟,分析了翼型的气动特性和转捩特点。利用红外成像法和压力敏感涂料(Pressure Sensitive Paint,PSP)测压技术对不同状态下的转捩位置和表面压力进行了风洞试验验证。研究结果表明:所设计的层流翼型在小升力系数下具有低阻、高升阻比的特点,在升力系数为0.3时,相比于初始翼型阻力降低了20.8%,升阻比提高了31.8%;翼型在设计状态下能够保持40%以上的层流区域,具有良好的层流控制能力。研究结果对民用飞机机翼减阻设计具有参考价值。

High subsonic aircraft could employ natural laminar airfoil to improve aerodynamic characteristics and reduce frictional resistance. A high subsonic laminar airfoil was designed in this paper. The flow field around the airfoil was studied based on γ-Re_θ transition model. Through numerical simulation method, postoptimality changes in aerodynamic characteristics and transition point of airfoil were studied. The infrared thermography technology and PSP pressure measurement technology were adopted to measure the transition point and surface pressure under different states in wind tunnel. The results show that the improved airfoil has the characteristics of low drag and high lift-to-drag radio under low lift coefficient. On condition that the lift coefficient is 0.3, it can reduce the resistance by 20.8% and increase the lift-to-drag ratio by 31.8%. The airfoil can maintain a laminar flow area of more than 40% in the design state, and has good laminar flow control capabilities. The research results can provide guidance to drag reduction design of civil aircraft.