上翼面扰流板偏转对冲压翼伞流场结构的影响  

作　　者：邵博 张强[1] 

机构地区：[1]中国飞行试验研究院,陕西西安710089

出　　处：《科技创新与应用》2022年第10期38-41,共4页Technology Innovation and Application

摘　　要：文章以Clark-Y翼型作为冲压翼伞的基础翼型,对上翼面扰流装置在不同下偏量情况下的翼伞流场进行二维定常数值模拟,详细分析扰流装置下偏对翼伞流场结构的影响。结果表明,扰流装置下偏时,在其后方形成较大的上翼面分离涡,上翼面出现完全流动分离时的迎角减小;前缘分离气泡在小迎角时对扰流板未下偏剖面的阻力系数影响较大;上翼面分离大涡的分布区域可合理解释大迎角下扰流板下偏剖面的阻力系数变化规律。文章对翼伞上翼面扰流装置的流场数值模拟研究有较强的指导意义。The Clark-Y airfoil is used as the basic airfoil of the ram air parachute,the two-dimensional steady numerical simulation of the parachute flow field of the upper surface spoiler under different downward deflection is carried out,and the influence of the downward deflection of the spoiler on the parachute flow field structure is analyzed in detail.The results show that when the spoiler deflects downward,a large upper surface separation vortex is formed behind it,and the angle of attack decreases at which there is complete flow separation on the upper surface;the leading edge separation bubble has a great influence on the drag coefficient of the non-spoiler-downward section at small angle of attack;the distribution area of the separated vortices on the upper surface can reasonably explain the variation law of the drag coefficient of the spoiler-downward section at high angle of attack.This paper has strong guiding significance for the numerical simulation of the flow field of the ram air parachute using upper surface spoilers.

关 键 词：冲压翼伞 扰流装置 流场结构 流场数值模拟 

分 类 号：V244[航空宇航科学与技术—飞行器设计]