大展弦比机翼的静气动弹性分析  

Static Aeroelastic Analysis for High-aspect-ratio Wing

作　　者：马艳峰[1,2] 贺尔铭[1] 李俊杰[2] 曾宪昂[2] 

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]中航工业第一飞机设计研究院,陕西西安710089

出　　处：《航空计算技术》2014年第3期53-57,共5页Aeronautical Computing Technique

基　　金：国家科技部国际合作专项项目资助(2013DFA80710)

摘　　要：大型飞机普遍采用的大展弦比机翼,其气动弹性问题显得尤为突出。通过求解基于三维结构网格的Euler/边界层耦合方程组,采用结构模态分析法,对HIRENASD机翼的静气动弹性进行了数值模拟。计算得到了机翼静弹变形前和变形后的压力分布以及不同攻角下翼尖变形值。计算结果和实验值对比分析,验证了Euler/边界层耦合方程组求解器对静气动弹性数值模拟的准确性,表明所发展的数值模拟方法可以用于大展弦比机翼静气动特性的分析研究。Currently,large aircraft commonly used for high aspect ratio wing ,which aeroelastic phenomena is particularly prominent .The static aeroelastic of HIRENASD wing is calculated through solving an Euler/BL equation based on the three-dimensional structure grid , the structure modal analysis is applied . The wing static aeroelastic prediction is computed when the wing is undeformed /deformed.Then,wing tip displacement was numerically simulated under the conditions of different attack angles .The results of simulation are compared with experiment data and further data analysis demonstrates the proposed method ′s validity and practicability .This method can be used to compute static aero-elastic analysis for high-aspect-ratio wing.

关 键 词：HIRENASD机翼 静气弹 Euler边界层 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]