The second phase of an investigation of the hinge moments of all-movable controls as used on cruciform missiles is described. In the first phase, an attempt was made to develop a hinge-moment prediction method as general as possible for speeds ranging from subsonic to hypersonic. In that work, the method was successfully applied for Mach numbers ranging from 1.3 to 3.7. In the present phase of the investigation, the methods from phase one, with some modifications, have been used to develop a procedure for determining the optimum fin planform and airfoil section to minimize the fin hinge moment over a range of Mach numbers, angles of attack, and fin deflection angles. The Mach numbers range is restricted to supersonic. The transonic speed range cannot be handled since methods are not presently available for predicting the center-of-pressure shift due to thickness in this speed range. Experimental data are not available to assess the accuracy of the method at hypersonic speeds.