This oblique configuration redistributes the shock waves that pile up in front of a plane at Mach speeds and cause drag.
这种倾斜的外形把超音速飞行时集中在飞机前部并形成阻力的冲击波重新分布。
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；
On the basis of one-dimensional stationary shock theory and perfect "effective gas" model, the effective drag coefficients are determinated experimentally by pressures of relaxation zone.
基于一维静止激波理论和理想“等效气体”模型，实验确定了粒子的有效阻力系数。
The results show that the shock standoff distance is increased and total drag coefficient and wall temperature are reduced with increasing external magnetic field.
结果表明，随着磁场的增强，激波脱体距离逐渐增加；总阻力系数和壁面温度逐渐减小。
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。
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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