This paper addresses the development of six degrees of freedom model for simulation of flight in the wake of a similar class aircraft. The aircraft considered in this study is a high performance fighter with full authority flight control laws. Apart from the aerodynamic effects, the flight dynamic model also includes a model of the air data system and the feedback control laws. The model is used to study the effect of wake on the flight dynamic response of the aircraft with and without effect of wake on the air data system feedback variables like angle of attack, angle of sideslip and static pressure.