For the past 2/2 years, under the sponsorship of the Air Materiel Command of the U.S. Air Force, GALCIT has been investigating the subject of the stresses in thin swept wings. The investigation has utilized theoretical, experimental, and electrical agencies on this problem. The problem has been reduced to a form amenable to theoretical analysis by assuming the wing replaced by a thin cantilever plate of uniform thickness. A theoretical solution of a thin cantilever plate of rectangular cross section with varying angle of sweep has been obtained. Expansion of the deflection in terms of the normal modes of vibrating bars is employed, the coefficients being determined by the Rayleigh-Ritz method. Experimental data for both stress and deflection are also presented. An approximate solution yielding the qualitative behavior of the stresses in such plates is included. The equations and circuits for the use of the electrical analog type of solution of plate problems are indicated, and a comparison is made between theoretical, experimental, and analog data, the latter being obtained by the use of a twelve-point electrical network.