弹道学报2011，Vol.23Issue(3)：58-62,5.
栅格翼翼身组合体超声速滚转阻尼特性
Roll Damping Characteristics for Missile With Grid Fins at Supersonic Speed
邓帆 1陈少松 1王学德1
作者信息
- 1. 南京理工大学能源与动力工程学院,南京210094
- 折叠
摘要
Abstract
N-S numerical simulation based on steady-state calculation was used to predict the roll damping characteristics of missile with grid fins at supersonic speed and different angles of attack.The result was compared with that of panel fins in order to find the different aerodynamic characteristics.The computational result of panel fins model by this method well agrees with the wind tunnel data found in foreign public papers.The method can be applied to simulating the roll damping characteristics of complex aircraft.The results indicate that the roll damping derivative of the missile with grid fin tails has two turning points as Mach number increases,and the serious flow chocking phenomenon appears while Ma=2.5.This derivative decreases as angle of attack increases,and the separated flow of the missile influences the leeward grid fin greatly.关键词
导弹/栅格翼/滚转阻尼导数/数值模拟Key words
missile/gird fin/roll damping derivative/numerical simulation分类
军事科技引用本文复制引用
邓帆,陈少松,王学德..栅格翼翼身组合体超声速滚转阻尼特性[J].弹道学报,2011,23(3):58-62,5.
