THEORETICAL CALCULATIONS OF THE PRESSURES, FORCES, AND MOMENTS DUE TO VARIOUS LATERAL MOTIONS ACTING ON THIN ISOLATED VERTICAL TAILS WITH SUPERSONIC LEADING AND TRAILING EDGES

摘要

Velocity potentials and pressure distributions due to various lateral motions are derived for a family of thin isolated vertical tails with arbitrary sweepback and taper ratio by applying linearized thin-airfoil theory for supersonic speeds. Motions considered in the analysis are steady rolling, steady yawing, and constant lateral acceleration. For the particular cases of triangular (half-delta) and rectangular vertical tails, integrated farces and moments expressed in the form of stability derivatives are also derived. All results are, in general, applicable at those supersonic speeds for which both the tall leading and trailing edges are supersonic. For purposes of completeness, anal¬ogous expressions and derivatives for sideslip motion obtained primarily from other sources are included.nExpressions for potentials, pressures, and stability derivatives are tabulated. Curves for the stability derivatives are presented, which enable rapid estimation of their values for given values of aspect ratio and Mach number. In order to indicate the importance of end-plate effects, several comparisons are shown of the derived results (based on a zero-end-plate analysis) with those corresponding to a complete-end-plate analysis.