摘要
基于2D可压N-S方程,对带扰流板的翼型绕流流场进行非定常数值模拟。分别对迎角及扰流板偏角对气动性能的影响做了分析,结果表明,扰流板偏角固定,随迎角增大,升力曲线线性良好,阻力在正迎角范围内的斜率小于负迎角;迎角相同,扰流板偏角越大,升力越小,阻力则越大。扰流板后的流场是一复杂的周期性旋涡脱落过程,主要由板梢涡和后缘涡主导,两者相互作用,形成周期性旋涡脱落。
The flowfield around an airfoil with a spoiler is numerically simulated in a time - accurate manner using a 2D compressible Navier-Stokes solver. The effect of attack angles and the spoiler deflection angles on time averaged aerodynamic coefficient are studied. The results show that at a fixed spoiler deflection, lift coefficient increases linearly with angles of attack, while the drag coefficient show nonlinear behavior more clearly with changing slopes at different angles of attack and the slope at positive angles is lower than that at negative angles. With the same angle of attack, lift coefficient decreases and drag coefficient increases with increasing 8 as expected. The flowfield around an airfoil with a spoiler is a complex periodical vertex shedding process that is dominated by vortices generated from spoiler tip and airfoil trailing edge. Two vortices affect each other to make the wake highly turbulent and oscillatory.
出处
《航空计算技术》
2006年第6期62-65,共4页
Aeronautical Computing Technique
