半模机翼振动的风洞实验技术研究  

Experiment Technology Investigation for Vibration of a Half Model Wing in Wind Tunnel

作　　者：解亚军[1] 叶正寅[1] 高永卫[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,西安710072

出　　处：《航空工程进展》2012年第1期39-43,共5页Advances in Aeronautical Science and Engineering

基　　金：国家自然科学基金(10872171)

摘　　要：飞行器机模型振动是影响其风洞实验数据可靠性的主要因素之一。为此,通过专门研制的半模振动模型,采用对称翼型NACA0012和层流翼型NACA64-210两种半模机翼进行了低速风洞振动实验。选取五种激振方式,用直接测力法得到模型在静态和不同激振方式下升力特性变化曲线,研究了振动频率、自然转捩和固定转捩、数据采集方式等参数对机翼气动特性测量结果的影响。结果表明:振动对半模机翼气动特性的影响程度因不同翼型构型、不同采集方式和翼面不同流动模式等而产生不同效果。结论对提高飞机模型风洞实验大迎角振动情况下的测量精准度有参考价值。Vibration of an air-vehicle model is one of factors that affect the reliability of test data in wind tunnel. Therefore a vibration test of half-model wing respectively with NACA0012 aerofoil and NACA64-210 aerofoil conducted in NF-3 wind tunnel is presented. Through the specially designed the elastic model with five exciting methods, the aerodynamic characteristics are investigated and analyzed by directly measuring force using a box balance. The affection factors, such as frequency, Reynolds number, boundary layer transition and data acquisi- tion mode, are investigated. It is shown that the lift aerodynamic characteristics of the half-model are affected by some factors,such as the aerofoil contour, the modes of data acquisition and boundary layer transition, etc. The conclusion is of guidance value on improvement of wind tunnel model test accuracy with vibration at larger angle of attack.

关 键 词：NACA0012半模机翼 NACA64-210半模机翼 升力特性 测力实验 静态 振动 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程]