The use of linked leading-edge and trailing-edge flap-type controls for the purpose of reducing hinge moments at supersonic speeds has been analytically investigated. A series of linked controls with supersonic leading and trailing edges on swept and unswept wings has been studied for Mach numbers of 1.414 and 1.960 by use of the linearized theory of supersonic flows. Variations of lift, rolling moment, and hinge moment with control deflection for these control combinations have been calculated, and the effect of finite wing thickness on these quantities has been estimated. Control characteristics have been tabulated for the condition of equal leading-edge and trailing-edge flap deflection, and the deflection ratios necessary for zero resultant hinge moment have also been listed.
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