不同尾翼鸭式布局远程弹在跨/超声速的气动特性实验研究  

Investigation of aerodynamic characteristics of canard-configuration long-range missile with different tails in transonic and supersonic flow

作　　者：邓帆[1] 陈少松[1] 谭献忠[1] 徐涛 

机构地区：[1]南京理工大学动力工程学院,南京210094 [2]南京模拟技术研究所,南京210016

出　　处：《实验流体力学》2010年第2期46-50,共5页Journal of Experiments in Fluid Mechanics

摘　　要：为了研究鸭式布局远程弹尾翼对气动特性的影响,设计了无尾翼,'T'型尾8翼,栅格尾翼三种尾翼布局,通过风洞测力实验研究不同布局在不同马赫数及迎角状态下对远程弹气动特性尤其是滚转特性的影响。实验结果显示:安装'T'型尾翼的模型和安装栅格尾翼的模型相比,在跨声速阶段,其升力特性优于栅格尾翼,也更利于滚转控制,但在超声速区域,栅格尾翼模型具有明显的升力特性优势,同时也容易进行滚转控制,而减小阻力是栅格翼将来需要解决的问题。Different tails were designed for canard--controlled long-range missile including nofins, ＂T＂ shaped fins and grid fins, investigated the influence of the long-range missile＇s aerody- namic characteristics especially the rolling characteristics of different tails at different speeds and attack angles with wind tunnel test. The results indicated that compared with the missile with grid fins, the missile with ＂T＂ shaped fins showed good lift characteristics and rolling characteristics in transonic flow, the lift characteristics of the missile with grid fins performanced excellent and it＇s capable of executing the roll control in supersonic flow, and it＇s important to reduce the drag of grid fins in the future.

关 键 词：鸭式布局 栅格翼 气动特性 滚转控制特性 风洞实验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程] V211.74