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。
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