NATIOIUL ADVISORY C-TTEE FOR

A method is presented for calculating the steady-state rolling effectiveness of ~lexible sweptback wings at subsonic and supersonic speeds. The present method was derived by reducing the problem to its simplest terms. The result is a procedure which possibly is as simple as can be devised, and which, based on conprisons with experiment, apparently is sti ~ capable of providing estimates of the changes in aileron rolli & effectiveness for a wide range of wing-aileron configu-rations within the experimental accuracy. As an aid to rapid calculation, the results of this investigation are presented in nondimensional form and have been c~c~ted for a tide range of tapered wings varying from O to 1.0 h taper ratio, for wing-span-body-diameter ratios of O, 0.2, and 0.4, and for ailerons of any spanwise extent and location. These calculations were made assuming that the wings were of homogeneous construction. The direct application of the results of this investigation to wings wherein the structural param