Mathematical modeling constitutes one of the recognized simulation techniques that can be employed in systems analysis. In an earlier work [I ], a six degrees-of-freedom simulation model had been utilized for missile airframe resonances extraction from its transient response. In the present work, the complete transfer function of the airframe is predicted. The analysis is extended to cover the missile autopilot. The obtained results show that the missile airframe can accurately be described by a linear second order system with two complex conjugate poles and two complex conjugate zeros. The airframe characteristics are sensitive to speed variations. However, this effect can be reduced by the utilization of autopilot with accelerometer and rate gyro in the feed back path.