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出 处:《振动与冲击》2015年第5期39-43,48,共6页Journal of Vibration and Shock
基 金:国家自然科学基金(11072198);高等学校学科创新引智计划(B07050)
摘 要:研究了microtab对翼型跨音速抖振始发特性的影响。采用SST湍流模型对RANS方程进行封闭,以NACA0012翼型为对象,用CFD方法计算了在其后缘附近安装microtab后,翼型的跨音速流场。对比分析了在翼型后缘附近的上表面、下表面单独安装和上下表面对称安装microtab后,对翼型跨音速抖振始发特性的影响,并研究了microtab的高度和弦向安装位置对跨音速抖振边界的控制作用。结果表明:在翼型后缘附近的上表面加装microtab能够提高抖振始发攻角,并且随着microtab高度的增加,抖振始发攻角有增大的趋势。在翼型后缘附近的下表面加装microtab能够提高抖振始发时的升力系数,且抖振始发时的升力系数随着microtab高度的增加而增大。microtab的弦向安装位置的变化对于抖振始发攻角影响较小,但是对抖振始发时的升力系数有明显的影响。A CFD simulation using Reynolds-averaged Navier-Stokes method with SST turbulence was conducted to determine the transonic flow around the NACA0012 airfoil with a microtab installed perpendicularly to the airfoil surface in the vicinity of trailing edge. The influences of different installing schemes of microtabs( one tap installed on airfoil upper surface,one tap installed on airfoil lower surface,two taps were symmetrically installed on airfoil upper and lower surfaces) on transonic buffet onset were analyzed and compared. Subsequently,a sensitivity analysis was conducted to determine the effect of height and chord wise position of microtab on transonic buffet onset. The results indicate that the improvement of the buffet onset angle of attack is achieved by installing the microtab on the upper( suction) surface of the airfoil; furthermore,the buffet onset angle of attack tends to be improved as the height of microtab increases; however,the improvement of the lift coefficient of buffet onset is attained by installing the microtab on the lower( pressure) surface of the airfoil; similarly,the lift coefficient of buffet onset can be improved with the increase in microtab height; the variation of microtab chord wise position has little effect on the buffet onset angle of attack,but it has obvious influence upon the lift coefficient of buffet onset.
分 类 号:TH211.412[机械工程—机械制造及自动化] TH211.3
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