Abstract: This thesis calculates integration performance of frontal inlet, chin inlet, two-dimensional inlet and missile. According to the drag coefficient, chin inlet and frontal inlet are superior to two-dimensional inlet, but the lift coefficient is the opposite. The inlet mass-flow coefficient of frontal inlet is the best, the flow coefficient of two-dimensional inlet is the lowest. By comparison of inlet total pressure recovery coefficient, attack-angle performance of chin inlet and two-dimensional inlet are superior to frontal inlet. 

Key words: Inlet; Missile body; Integration design; Performance

摘要： 对头部进气、颌下进气、二元(两侧)进气三种典型布局的进气道/弹体一体化性能进行了计算,就阻力系数而言,颌下及头部进气优于两侧进气,升力系数则恰好相反。头部进气的流量系数最高,颌下次之,两侧进气则最差。对不同布局的总压恢复系数进行比较,颌下及两侧进气则较头部进气有好的攻角特性。

关键词: 进气道;弹体;一体化设计;性能