摘要
采用数值模拟方法研究在设计点 (马赫数 6,迎角 0°)锥导乘波体气动外形的设计方法及其基本气动特性 ,以及在非设计点时该乘波体的气动特性 ,即各个气动系数随迎角和马赫数的变化特性 .研究表明 :基于无粘锥形流的乘波体气动外形的反设计方法是成功的 ;在设计点附近选取合适的半基准圆锥激波角并考虑粘性影响时 ,可得到乘波体最大升阻比为 3.36;给出了采用这一布局的单级入轨运载器的可行的飞行控制方案 ;
The design method and basic aerodynamic characteristics were studied by numerical simulation for cone-derived waverider at Mach 6 and attack angle 0. Off-design performance of the designed waverider were discussed, namely lift, drag and lift-drag ratio changing with Mach number and attack angle. The inverse-design method for the waverider configuration is based on inviscid conical shock wave. The biggest lift-drag ratio 3.36 considering viscous effects is obtained at Mach 6 when a proper base conical shock wave angle is chosen. A feasible flight control scheme is presented for the SSTO (single-stage-to-orbit) vehicle adopting this configuration. The favorable method of improving the lift-drag ratio of the figuration is brought forward.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2004年第5期429-433,共5页
Journal of Beijing University of Aeronautics and Astronautics
