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.
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；
In the second design step, improvement of wing's aerodynamic characteristic is mainly depended on the weakening of shock which reduces wave drag during the wing section optimization.
在平面形状优化基础上，在机翼容积不变约束下，再采用剖面翼型优化设计，通过机翼剖面细微变化弱化较大马赫数下的激波、减小激波阻力。
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