摘要
在M∞=6,30km高空条件下,以升阻比为目标函数,进行了锥形流乘波体的黏性优化设计,讨论了影响乘波体升阻比的因素,并对优化结果进行了数值验证．结果表明:对于升阻比最大的黏性优化乘波体,存在最优圆锥角使得源自该基本流场的乘波体升阻比最大;摩阻和波阻处于同一量级;体积率、细长比和展长比都随着基本流场圆锥角的增大而增大．
A family of optimized hypersonic waverider derived from conical flow fields is generated and studied; the detailed viscous effects are included within the optimization process using the reference temperature methods. A non-linear simplex method is used to find the waverider configuration for the maximum lift over drag ratio, viscous optimization is completed at Mach number 6, attitude 30km, and cone angle from 5° to 10°. Shapes of waverider with high lift over drag ratio are obtained, and the results are verified with CFD. The results show that for the optimized design waverider, the lift over drag ratio of waverider is the maximum at a certain cone angle; the skin friction drag and wave drag are nearly equal; volumetric efficiency, slenderness, span over length ratio increase with the cone angle.
出处
《力学学报》
EI
CSCD
北大核心
2006年第4期540-546,共7页
Chinese Journal of Theoretical and Applied Mechanics
基金
国家自然科学基金资助项目(90405012).~~
关键词
乘波体
优化设计
气动力
升阻比
waverider, optimized design, aerodynamics, lift over drag ratio
