This paper is meant to develop a procedure to construct an analytical aero-dynamical model for subsonic flight of an aircraft. Idea is to present the aero-dynamic coefficients of forces and moments acting on the aircraft that can be used to simulate them as functions of controlling variables. The procedure presented is based on data obtained from wind tunnel measurements of the longitudinal and lateral dynamics of the aircraft. The model works well not only in the non-linear region of the angle of attack and side slip, but also includes the stall phase due to large control angle deflections. Further, it incorporates the additive aerodynamic asymmetries. Computer model of resulting equations can be employed in a 6dof simulation and dynamics of the aircraft is predicted.