机翼大攻角下失速颤振的气动弹性研究

工程热物理学报 , 2002, 23(5): 573-575.

1.清华大学热能工程系,北京,100084

2.清华大学热能工程系,北京,100084

3.北大学流体科学研究所,仙台980-8577日本

基金项目: 国家重点基础研究发展计划(973计划)(G1999022306) 国家自然科学基金(50076019)

AEROELASTIC ANALYSIS OF AN AIRFOIL'S STALL FLUTTER AT LARGE MEAN INCIDENCE ANGLE

本文采用流固耦合的数值方法研究了机翼在0°～50°攻角下的颤振.计算结果表明,随着来流攻角α0的增大,机翼的固有频率对颤振的影响越来越大,颤振由线性的强迫振动逐渐发展成为非线性的自激振动,而当α0增加到一定程度以后,大尺度分离流交替地从机翼头部和尾部产生,机翼和流场会发生共振,引起机翼的失速颤振.

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