Abstract
The distribution of lift between the wing and tail surfaces of a conventional aircraft is examined in order to determine that which would produce the minimum drag for a given lift. Further, the center of gravity position is determined which gives the desired lift distribution and, at the same time, maintains aircraft trim. Analytical expressions are developed which clearly show the dependence of this optimal e.g. position on the various aerodynamic and geometric parameters. In particular, it is shown how large changes in position of the optimal e.g. position can occur for small changes in the tail downwash angle. Numerical results are presented for a small twin-engine aircraft.
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