具有乘波侧缘的高超声速飞行器气动外形设计  

Aerodynamic Configuration Design of Hypersonic Vehicle with Waverider Sides

作　　者：李晓宇[1] 丁国昊[1] 李桦[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《弹箭与制导学报》2008年第4期175-177,202,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了保持高超声速发动机流道构形,利用锥导乘波构形设计方法设计乘波侧缘与中心流道一体化构形构成高超声速飞行器基本构形,对设计构形的乘波特征进行了数值验证,利用乘波构形在高马赫数下的过渡乘波特性,采用变马赫数设计,设计了不同的乘波侧缘与中心流道一体化构形,研究表明通过该方法可以快捷的获得完全乘波的构形作为高超声速飞行器一体化构形。The cone derived waveriders were designed to be integrated with central flow path of scramjet. The aerodynamic characteristics of the configurations were validated by CFD simulations. Considering that a waverider can ride over the shock wave at a higher Mach number than the designed, a completely waverider configuration was obtained by integrating central flow path with waverider sides designed at lowed Mach numbers. Integrated configurations with waverider sides were presented as candidates of hypersonic vehicle configurations.

关 键 词：高超声速 乘波构形 数值模拟 一体化 

分 类 号：TJ760.11[兵器科学与技术—武器系统与运用工程]