高超声速锥导乘波体流场的数值模拟研究  

Numerical Simulation on Hypersonic Flowfield of Cone-derived Waverider

作　　者：赵志[1] 宋文艳[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《弹箭与制导学报》2009年第5期170-172,共3页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：航天科技创新基金资助

摘　　要：为了验证乘波体的设计方法,对设计马赫数6的锥导乘波体的三维流场进行了数值模拟。研究表明:设计点无粘流场与基准流场吻合,符合乘波体的设计理论;粘性对锥导乘波体的升力系数的影响不大,对阻力系数有较大影响;数值模拟方法对乘波体的流场和性能计算是适用的。For validating the design method, numerical simulation was performed on the cone-derived waverider at Mach number 6. The result indicates that the flow field from numerical simulation compared with the basic flow field. Viscous has a great effect on the drag coefficient of cone-derived waverider, and has no clear effect on lift coefficient. The nu- merical method is efficient for cone-derived waverider.

关 键 词：高超声速 乘波体 数值模拟 升力 阻力 

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]