高速自然层流翼型的设计与风洞实验研究(英文)

为了发展商务客机用的低阻力翼型,本文在荷兰科技大学TST27风洞开展了高速自然层流翼型的实验研究工作。为了减小测量技术对模型流场的干扰,提高测量精度,分别采用了IR,PIV以及阴影法等非接触测量技术。通过这些非接触测量技术的使用,对翼型的转捩位置、后缘分离以及升阻力等气动特性进行了测量研究。从实验结果可以看出,在小迎角范围内,翼型可以在其表面保持较长的层流段,并且后缘分离涡不会随迎角增大而向前发展,使翼型具有高升力、低阻力的特性。从实验结果和计算结果的差别可以看出,实验数据是可靠的,设计的翼型基本满足了设计要求。

A High-speed Nature Laminar Flow Airfoil and Its Experimental Study in Wind Tunnel with Nonintrusive Measurement Technique

This article deals with an experimental study on the aerodynamic characteristics of a low-drag high-speed nature laminar flow (NLF) airfoil for business airplanes in the TST27 wind tunnel at Delft University of Technology, the Netherlands. In this experiment, in an attempt to reduce the errors of measurement and improve its accuracy in high-speed flight, some nonintrusive measurement techniques, such as the quantitative infrared thermography (IRT), the digital particle imaging velocimetry (PIV), and the shadowgraphy, are applied to obtain precise data about transition locations, separation on trailing edges, and lift/drag characteristics. The experimental results reveal that, in the high-speed flight, small angles of attack are helpful in retaining long laminar flows, preventing the vortex at the trailing edge from moving forward and thus imparting the airfoil and the high-lift and low-drag characteristics. The comparison of the measured results to the calculated ones proves the acceptability of the airfoil and its aerodynamic characteristics satisfying the design requirements.