高超声速锥导乘波体非设计点性能研究  

Numerical Simulation on Off-Design Performance of Hypersonic Cone-Derived Waverider

作　　者：赵志[1] 宋文艳[1] 肖隐利[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《飞行力学》2009年第1期47-50,共4页Flight Dynamics

摘　　要：对设计马赫数6的锥导乘波体在马赫数4~7、迎角-6°^+6°的三维流场进行了数值模拟。研究表明:粘性对阻力系数的影响较大;非设计马赫数时,锥导乘波体的升阻比没有明显减小;升力系数与迎角呈线性关系,随着迎角增大而增大;升阻比在+2°迎角下达到最大。Numerical Simulation was performed on the cone-derived waverider with design Mach number of 6. The calculations studied both design and off-design conditions, including angles of attack from - 6 to ＋ 6 degrees at the design Mach number and at the off-design Mach numbers of 4, 5 and 7 at zero angle of attack. The effects of flight Math numbers and angles of attack are analyzed. The result shows that the viscosity has a great effect on the drag coefficient of a cone-derived waverider. The lift coefficient increases linearly with angles of attack. There is no significant degradation of lift-to-drag ratio at off-design Mach numbers. The maximum lift-to-drag ratio occurs at an angle of attack of ＋ 2 degrees.

关 键 词：高超声速 乘波体 升阻比 数值模拟 非设计点 

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]