Abstract
This paper deals with a theoretical analysis on the aerodynamic forces due to the potential flow on the delta wing, and deduces that the potential flow lift coefficient in the delta wing will have a certain maximum value according to the conditions. The studies on the limit of the lift coefficient for the conventional wing with the high aspect ratio have been published in some papers, but there exists little paper on that for the slender wing with the low aspect ratio as the delta wing. The results in the present paper will offer an available guide for the improvement of the STOL characteristics in the high speed aircraft.
