大展弦比机翼低速静气动弹性模型的设计、制作和风洞试验

Design,manufacture and low speed wind tunnel test of a high aspect ratio wing static aeroelastic model

通过弹性相似模型的风洞试验研究大展弦比机翼在弹性变形下的气动特性是研究飞机静气动弹性特性的重要手段。发展了一种静气动弹性模型低速风洞试验技术,针对某大展弦比机翼,设计、制作了缩比弹性结构相似模型,在南京航空航天大学NH03风洞进行了低速静气动特性风洞试验。详细介绍了弹性模型的各项技术和风洞试验结果,结果表明该项技术适合大展弦比机翼静气动弹性特性的研究,试验结果可作为大展弦比机翼设计的重要参考。

For a high aspect ratio wing, it is important to investigate the characteristic of aero- dynamics in large elastic deformation. A significant way is to execute the test in wind tunnel using scaled elastic structure similar model. In this paper, a kind of static aeroelastic model tes- ting technique in low speed wind tunnel was developed. A scaled elastic structure similar model was designed and manufactured for a high aspect ratio wing, and the test was performed in NU- AA（ Nanjing University of Aeronautics and Astronautics） NHO3 wind tunnel. The paper describes the details of the elastic model technology and gives the results of the wind tunnel test. It indicates that the elastic model technology is suitable for investigating static aeroelasticity characteristics of a high aspect ratio wing and the results of the wind tunnel test is significant for high aspect ratio wing.