The ability to empirically allocate the spanwise distribution of thickness across a wing during the earliest phases of conceptual design is extremely useful. Quantitative statistical design for system optimization studies requires a reliable allocation process, directly traceable to a final loft. In choosing the local section thickness ratio of a wing, there are multiple considerations which are at first, somewhat unintuitive to make. For each strip, from root to tip, the allowable wing thickness as well as the necessary camber and incidence depends broadly upon the local lift the strip must sustain as well as the design Mach number for the incoming flows. The difficulty in developing a concise technique or equation to simultaneously determine thickness and camber stems from a cross-coupling of common design variables. A statistical study of potential flow solutions lead to develop a technique which the reader may use to supplant the Korn Equation, choosing specific rather than generalized theoretically attainable airfoils to meet specific lift and critical Mach number conditions. Subtle, yet important, non-linearities were found in the coupling between allowable thickness, critical Mach number and design lift coefficient.
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