An aerodynamic analysis model for an airframe/propulsion integrated module was established based the theory of oblique-shock

in conjunction with a quasi～-1Dengineering estimation and the method of characteristics.The viscosity effects of the module were taken into account using the method of reference temperature.Aparametric analysis was then performed using the developed model.The influences of the design parameters

including the fore-body length

the leading angle

and the width of the module upon the aerodynamic characteristics were presented.The results reveal that increasing the length of the fore-body will make the thrust and the lift

as well as the specific impulse of the module to increase first and then decrease;increasing the leading angle will increase the lift but decrease the thrust;increasing the width of the module will decrease the equivalence lift.Hence

modularized propulsion system and the trade-off among these variables must be taken into account in the configuration design of the hypersonic cruise vehicle.