Gust-load factors are calculated for tailless airplanes by a simplified method tha t includes directly the effect of the pitching motion. The calculations are made for a wide range of mass parameter (a quantity that includes both wing loading and chord), center of gravity position, and pitching radius of gyration. A linear gust with the maximum gust velocity a t the critical distance of eight chord lengths is used. Although certain assumptions are made in order to simplify the calculations, it is shown tha t for a typical case the results agree with the results obtained by a rigorous solution. The application of the results to tailless airplane design is illustrated by typical curves showing the variation of the limit load factor with wing loading for various values of center of gravity position and radius of gyration. I t is found tha t the load factor is reduced by a forward movement of the center of gravity or by a reduction of the radius of gyration. For example, a representative case shows that , for a range of mass parameter from 5 to 30 (a variation of wing loading from 10 to 60 lbs. per sq.ft. for a 12ft. chord), a movement of the center of gravity of 5 per cent chord forward of the aerodynamic center causes reductions of the limit load factor of 26, 11, and 3 per cent, for values of the ratio of the radius of gyration to the chord of V-i, A, and 1, respectively.