空气动力学学报2017，Vol.35Issue(6)：841-845,5.DOI:10.7638/kqdlxxb-2015.0075
大展弦比机翼跨声速静气动弹性风洞试验
Wind tunnel test on transonic static areoelasticity of high-aspect-ratio wing
郭洪涛 1陈德华 2吕彬彬 1余立 2祖孝勇2
作者信息
- 1. 中国空气动力研究与发展中心 空气动力学国家重点实验室,四川 绵阳 621000
- 2. 中国空气动力研究与发展中心 高速空气动力研究所,四川 绵阳 621000
- 折叠
摘要
Abstract
Static aeroelasticity has great influence on the aerodynamic performance and safety of aircrafts. Based on a wing-body model for aerodynamic/structural similarity, a static aeroelastic wind tunnel test was carried out to research the transonic static aeroelastic effects. The results show that the static aeroelasticity has significant influence on the aerodynamic performance for the hypercritical high-aspect-ratio sweepback wing at its designed cruise point. The static aeroelastic effects lead to 21% decrement in the lift coefficient,8% increment in the lift-drag ratio,and the forward movement of the aerodynamic centre about 1%b A .With the Mach number higher than the designed cruise value,the static aeroelastic effects worsen the wing′s aerodynamic performance. In addition, in transonic range, the Mach number and dynamic pressure have significant influence on the static aeroelastic effects,and the influence has nonlinear characteristics.It is difficult to precisely predict the influence law and magnitude by current theory.关键词
静气动弹性/大展弦比机翼/跨声速流动/风洞试验/气动特性Key words
static aeroelasticity/high-aspect-ratio wing/transonic flow/wind tunnel test/aerodynamic performance分类
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郭洪涛,陈德华,吕彬彬,余立,祖孝勇..大展弦比机翼跨声速静气动弹性风洞试验[J].空气动力学学报,2017,35(6):841-845,5.
