Theoretical force and moments due to sideslip of a number of vertical tail configurations at supersonic speeds

John C. Martin, Frank S. Malvestuto, Jr.
Sep 1951

Formulas have been obtained by means of the linearized supersonic-flow theory for the lateral force due to sideslip C(Y)(B), the yawing moment due to sideslip C(n)(B), and the rolling moment due to sideslip C(l)(B) for normal tail arrangement consisting of rectangular, triangular, and sweptback vertical tails of arbitrary taper and sweep mounted symmetrically on a horizontal tail of arbitrary shape.

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