In order to study the effects of the airborne ballistic characteristics of wake simulation rockets on the simulated wake area, the exterior ballistic model of the rocket projectile, the space motion differential equation of the resistance plate and the engine, the force model of the connecting rope were established. The differential equations of space motion in the whole process of uncontrolled flight, air steering, air separation and unfolding of the detonating cable were obtained. The whole trajectory of the tail-flow-simulated-rocket was simulated and analyzed. The effect of different initial firing elements on the air trajectory of the detonating cable was emphatically analyzed. The influence of initial launch angle, the number of pulse tubes, the ignition time and the rocket separation time on simulated wake generation region were investigated. The simulation results show that the range and maximum shot height of the rocket projectile are relatively reasonable when the initial launch angle is 15 degrees. The angle of the rocket′s air steering depends on the total impulse of the pulse engine and has nothing to do with the ignition time. The effect of air separation time on the water foaming area of the detonating cord is not obvious. Air steering and separation should be completed as soon as possible when the steering requirements and the requirements of the foamed area are met.