翼型纵向俯仰非定常气动力研究

飞行器飞行时受到的非定常气动力是飞行器设计以及机动飞行中须考虑的一个重要因素。采用CFD方法数值模拟了NACA0012翼型在马赫数从0.2~5.0范围变化时做强迫振荡的非定常流场。通过积分法计算了在不同马赫数时翼型的俯仰动导数。计算结果表明,迟滞效应随马赫数的增大先增大后减小,在跨声速区域迟滞效应达到最大;迟滞环的绕向在跨声速区域为顺时针方向;迟滞环顺时针绕向时,动导数大于零,模型动不稳定,逆时针绕向时,动导数小于零,模型动稳定;旋转角速度越大,翼型表面非定常气动效应越明显。

Study of hypersonic airfoil pitch oscillation unsteady aerodynamic force

Unsteady aerodynamical force should be considered as an important factor during vehicle design and maneuver flight.The simulation of the unsteady flow field of the NACA0012 airfoil with forced oscillation when Mach numbers range from 0.2 to 5.0 by the CFD means.Provide pitch dynamic derivatives with different Mach numbers by integration procedure.The results show that the hysteresis loop first gets large and then small with Mach numbers increasing,and in transonic area the hysteresis loop reaches up to the ...