Equations and Charts for the Rapid Estimation of Hinge-Moment and Effectiveness Parameters for Trailing-Edge Controls Having Leading and Trailing Edges Swept Ahead of the Mach Lines

摘要

Existing conical-flow solutions have been used to calculate the hinge-moment and effectiveness parameters of trailing-edge controls having leading and trailing edges swept ahead of the Mach lines and having streamwise root and tip chords. Equations and detailed charts are presented for the rapid estimation of these parameters. Also included is an approximate method by which these parameters may be corrected for airfoil-section thickness. Deflected controls are assumed to be located either at the wing tip or far enough inboard to prevent the outermost Mach lines from the controls from crossing the wing tip. For either of these locations, the innermost Mach lines are assumed not to cross the wing root chord. The method for determining control hinge moment resulting from wing angle-of-attack loading is valid for wing plan forms having the leading edges swept ahead of the Mach lines and having streamwise tips. The only additional restrictions are that the controls must not be influenced by the tip conical flow from the opposite wing panel or by the interaction of the wing- root Mach cone with the wing tip.