Then, the base bleed method is introduced on a general supersonicmissile to decrease the base drag of the inlet cowl for the first time and is validated by wind tunnel test.
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.