Theoretical calculations of the lateral force and yawing moment due to rolling at supersonic speeds for sweptback tapered wings with streamwise tips supersonic leading edges

Sidney M. Harmon, John C. Martin
naca-tn-2156
Jul 1950


Theoretical results are obtained, by means of the linearized theory, for the lateral force and yawing moment due to combined angle of attack and roll. The thin wings considered are tapered and have leading and trailing edges which are each swept at a constant angle; the tips are parallel to the center section.

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