翼面气动外形对栅格翼减阻的影响  

On the Influence of Wing Aerodynamic Surface on the Grid Fin Drag Reduction

作　　者：谭献忠[1] 邓帆[2] 陈少松[1] 

机构地区：[1]南京理工大学能源与动力工程学院,江苏南京210094 [2]中国运载火箭技术研究院空间物理重点实验室,北京100076

出　　处：《实验力学》2013年第2期255-260,共6页Journal of Experimental Mechanics

摘　　要：从节约空间的角度考虑,带一定弧度的翼面有利于栅格翼在弹体上的安装。通过风洞实验研究了两种不同安装方式的弧形翼面栅格翼的气动特性,并和翼面无弧度的栅格翼进行比较。结果显示,弧形翼面的栅格翼阻力系数均小于翼面无弧度的栅格翼,升阻比除跨音速阶段外比后者表现更好,同时对一种前缘后掠的栅格翼模型进行了数值计算,比较研究结果显示,对栅格翼的迎风面栅格进行一定角度的后掠能有效减小超音速阶段的波阻,是一种栅格翼减阻设计的新思路。From the consideration of space saving,airfoil with a certain arc is of benefit to gird fin installation.The aerodynamic characteristics of two grid fins with curved wing surface and different installations were experimentally investigated by wind tunnel test,and were compared with the conventional grid fin without arc.Results indicate that the drag coefficient of two curved grid fins was smaller than that of conventional fin,the lift-to-drag ratio of the former is better than that of the latter except of transonic stage.Grid fin with windward swept was also numerically investigated.Results showed that grid fin with certain windward swept angle can reduce wave drag obviously,which provides a novel design for drag reduction of gird fin.

关 键 词：栅格翼 弧形翼面 升阻比 波阻 

分 类 号：TJ760.3[兵器科学与技术—武器系统与运用工程] O355[理学—流体力学]