跨声速机翼操纵面非定常气动力Euler方程计算  

Unsteady Transonic Flow Computation for a Wing with Control Surface Deflections by Euler Equations

作　　者：董璐[1] 郭同庆[2] 

机构地区：[1]中国人民解放军理工大学理学院,江苏南京211101 [2]南京航空航天大学航空宇航学院,江苏南京210016

出　　处：《飞机设计》2009年第4期18-21,共4页Aircraft Design

摘　　要：采用代数法与椭圆型方程优化相结合的结构生成方法为带操纵面F5机翼生成面对接块结构网格;弹性变形技术生成动态网格;有限体积法、双时间推进法求解非定常Euler方程。给出一种适于面对接块结构网格计算的守恒量插值方法。数值计算了F5机翼操纵面作简谐运动时的非定常气动力,计算值与试验值吻合较好。Both algebraic method and optimal elliptic partial differential equations are used to generate face - patched multiblock grids for F5 wing with control surface deflections. Dynamic grids are generated by the use of a deforming technique. The finite volume method and dual time - stepping approach is used to solve unsteady Euler equations. An effective interpolation method for conservative variables on discontinuous faces is developed for face -patched muhiblock grids. The computational results about unsteady transonic forces on control surface are in agreement with experimental data.

关 键 词：块结构网格 EULER方程 有限体积法 双时间推进法 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]