The problem of aerodynamic parameters estimate was focused on.

On the basis of the simulation results, aerodynamic parameters are analyzed, and the optimal design of the aerodynamic shape can be obtained.

From the aspects of stability margin and aerodynamic parameters, this paper states that aerodynamic coupling is the dominant reason why missile s control system on the condition of large angle of attack is unstable.

The effects on the forces between two stages of some aerodynamic parameters were analyzed,and through reasonable designation of the aerodynamic figure of the missile,the forces between two stages could be reduced effectively.

The change rules of aerodynamic parameters including lift coefficient,drag coefficient and pitch moment coefficient have been analyzed when angle of attack and fuel flow rate is changed.

According to the rigid body trajectory model of finless-aerial-bomb under the ideal conditions,the influences of aerodynamic parameters on the motion of centroid and angle of finless-aerial-bomb were analyzed by theoretical simulation.

The aerodynamic coefficients were estimated by using STF.

The results show that this technique is useful for quick determination of aerodynamic coefficients, and particularly applicable to nonlinear flight regimes, such as high angle of attack regime.