THEORETICAL FORCE AND MOMENTS DUE TO SIDESLIP OF A NUMBER OF VERTICAL TAIL CONFIGURATIONS AT SUPERSONIC SPEEDS

Formulas have been obtained by means of the linearized supersonic-flow theory for the lateral force due to sideslip Cy, the yawing moment due to sideslip C „ , and the rolling moment due to sideslip C7 for ß ß normal tail arrangements consisting of rectangular, triangular, and sweptback vertical tails of arbitrary taper and sweep mounted symmetri-cally on a horizontal tail of arbitrary shape. The results are restricted to cases where the leading edges are supersonic and the Mach line from the tip of the leading edge of the vertical tail does not intersect the root section. The effect of the horizontal tail on the derivatives was evaluated for the cases where the Mach line from the leading edge of the root section cuts the trailing edge of the vertical tail. A series of design curves is presented which permits rapid estimation of the lateral force due to sideslip Cy, the yawing moment due to sideslip C _ , and the rolling moment due to sideslip C7. ß 4