1·Then, the base bleed method is introduced on a general supersonic missile to decrease the base drag of the inlet cowl for the first time and is validated by wind tunnel test.
本文首次将底部排气法应用于导弹上，结合一种具有常规气动布局的超声速导弹进行了底部排气方案设计，采用一种“底窝器”来提高进气道整流罩的底部压强，并进行了风洞实验验证。
2·These conclusions can be used for system design of rotating missile in the attitude control system and selection of structure and pneumatic parameters for supersonic fluidic elements.
所得结论可为旋转弹姿态控制系统的总体设计以及超音速射流元件的结构及气动参数选择提供依据。
3·For a missile with supersonic inlets, there's complicated aerodynamic interference between body and inlets, and this aerodynamic interference is difficulty to analysis in theory.
对于有超声速空气进气道的导弹，导弹弹身和进气道之间存在着复杂的气动干扰，这种干扰难以从理论上进行精确分析。