Airplane motion in subsonic and supersonic potential flow field has been considered in this paper. Aerodynamical forces and moments, present in the differential equations of motion, dependent on the center of gravity velocity, angular velocity of airplane and its inclination relative to the direction of the velocity vector, have been calculated on the basis of potential flow theory by the panel method application. Boundary conditions on the airplane surface have been modified by introducing the influence of the angular velocity. Fifth order Verner-Runge-Kutta method has been used in the numerical solution of the initial value problem. Numerical results of the computation are illustrated by the appropriate flight simulation examples.