摘要
为了实现飞行器新型动态特性控制,提出了一种基于尾缘的低频大功率合成射流致动器的设计方案。通过数值方法对该尾缘合成射流工作下的NACA0012翼型的非定常流场进行了模拟。研究了不同开口形式,喷流动量系数和减缩频率对翼型的升力、阻力和力矩特性的影响。研究表明尾缘处低频大功率合成射流激励能有效改变翼型的升力和力矩特性,动量系数的增加会增大升力和力矩系数的最大值,而减缩频率的增加会使升力和力矩系数的最大值减小,且翼型气动特性系数的滞后角也会随减缩频率的增加而增大。
In order to obtain a new device for aircraft dynamic control, a low frequency, high-power syn thetic jet set in trailing edge is presented. The unsteady flow of NACA 0012 airfoil with the synthetic jet set in trailing edge is simulated by numerical method. The effects of orifice form, jet momentum coefficient and reduced frequency on lift coefficient and moment coefficient are studied. It is demonstrated that the low fre- quency, high-power synthetic jet set in trailing edge can modify the lift and moment effectively. The ampli- tudes of lift and moment increase with the jet momentum coefficient, while decrease with reduced frequency, and the phase delay of the airfoil aerodynamic characteristic coefficient will be increase with the reduced frequency.
出处
《空气动力学学报》
EI
CSCD
北大核心
2012年第5期606-612,共7页
Acta Aerodynamica Sinica
基金
国家自然科学基金(10802063)
航空基金(2009ZA53009)
西北工业大学基础研究基金
翱翔之星人才计划
关键词
合成射流
数值模拟
非定常流
翼型
synthetic jet
numeral simulation
unsteady flow
airfoil
