NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER
An investigation was made of the effects of 0.30-aileron-chord tabs on an NACA 66,2-216 a 0.6 airfoil equipped with a 0.20-airfoil-chord plain sealed aileron. The aileron profiles considered consisted of one profile conforming to the normal NACA 66,2-216 a 0.6 ordinates and a profile consisting of straight-line surfaces from the trailing edge to the hinge-line ordinates of the aileron. Basic data are presented from which the effect of tabs can be calculated for specific cases. The data are sufficient for the solution of problems of fixed tabs with a differential linkage, as well as simple and spring-linked balancing tabs.