吸气式二元翼型风洞的气动设计

Aerodynamic Design of the Aspirating Two-dimensional Airfoil Wind Tunnel

翼型是机翼等气动部件的二维截面,对于机翼乃至飞行器全机的气动性能都有着重要影响,所以翼型研究是先进飞行器设计的基础和重点。翼型风洞是进行翼型实验的最适用风洞,在翼型研究中发挥着不可替代的作用,但由于其专用性,目前关于翼型风洞设计的公开成果并不多见。基于翼型实验的参数要求,综合运用空气动力学知识,确定了一种吸气式二元翼型风洞的气动设计方案。设计的翼型风洞包括动力段、扩压段、实验段、收缩段和稳定段等洞体,并配有阻尼网、蜂窝器等内部整流装置。经过计算和分析,结果表明此风洞具有结构紧凑、湍流度低、能量利用率高的优势,可以较好完成翼型实验,推动飞行器技术发展。

Airfoil is a two-dimensional section of the airfoil,which has an important impact on the aerodynamic performance of airfoil and the whole aircraft.Therefore,airfoil research is the foundation point of advanced aircraft design.Airfoil wind tunnel is the most suitable wind tunnel for airfoil experiment and plays an irreplaceable role in airfoil research.However,due to its specificity,there are few public results on airfoil wind tunnel design.Based on the parameter requirements of airfoil experiment and the knowledge of aerodynamics,a aerodynamic design of the aspirating two-dimensional airfoil wind tunnel is determined in this paper.The designed airfoil wind tunnel consists of a power section,a diffuser section,an experimental section,a contraction section and a stability section,and is equipped with internal rectification devices such as damping nets and honeycomb.After calculation and analysis,the results show that the wind tunnel has the advantages of compact structure,low turbulence and high energy efficiency,which can better complete the airfoil experiment and promote the development of aircraft technology.