稳定射流环量控制的仿真研究

摘要

为改善飞行器的升阻特性，提高其机动性能，利用数值仿真技术对稳定射流在超临界翼型的作用效果进行研究。通过动量系数变化对环量控制作用效果影响规律的研究分析后发现：稳定射流环量控制与无射流情况对比，有较强的优越性，在小迎角或负迎角就可以产生较大的升力。通过对后缘半径和射流口高度的变化对环量控制作用效果影响规律的研究分析，得到圆形后缘超临界环量控制翼型的初步设计方法。计算结果可为进一步研究环量控制对飞行器的影响奠定理论基础。%In order to improve aircraft′s lift-drag characteristics and motor performance ,through the nu-merical simulation technology , effect of circulation control by steady jet on supercritical airfoil is re-searched .Through researching and analyzing the influent law of circulation control effect by changing the momentum coefficient , the results show that compared with the no blowing , the circulation control by steady jet is much better ,a larger lift can be obtained at a lower or negative attack angle .Through researc-hing and analyzing the influent law of circulation control effect by changing the trailing edge radius and height of jet slot ,the preliminary design method of supercritical airfoil on round edge is obtained .The cal-culation results can be used as theoretical basis of further research work of circulation control effect on aircraft.