高升阻比乘波体外形设计及气动特性计算研究

 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;分析提出了进一步提高该乘波体气动布局升阻比的有效途径.

Design and computational study of waverider configuration with high performance

The design method and basic aerodynamic characteristics were studied for cone derived waverider at Mach 6 and attack angle 0. Off design performances of the designed waverider were also discussed, namely lift, drag and lift drag ratio changing with Mach number and attack angle. All the research works were finished by numerical simulation method. Results show that: the inverse design method for the waverider configuration is successful 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.