Theoretical Lift and Damping in Roll of Thin Wings With Arbitrary Sweep and Taper at Supersonic Speeds. Supersonic Leading and Trailing Edges

摘要

Generalized expressions are obtained by means of the linearized theory for the surface velocity potentials and the surface-pressure distributions due to lift and roll, the lift-curve slope, and the damping-in- roll derivative for a series of thin wings. The results are applicable to wings of arbitrary taper ratio in which the leading edge is sweptback, whereas the trailing edge is either sweptback or swept- forward (including zero sweep angles), and the tips are unyawed with respect to the free-stream direction. The range of speeds covered is such that the components of the stream velocity normal to the leading and trailing edges are supersonic. A further restriction is that the foremost Mach line from either tip may not intersect the remote half- wing. The configurations for which the results for the stability derivatives are applicable may be extended by means of the reversibility theorem. These additional configurations include cases in which the foremost Mach line from either tip intersects the remote half-wing, provided the Mach line from the leading edge of the center section intersects the trailing edge, and also wings which have sweptforward leading edges. The results of the investigation are presented in the form of generalized design curves for rapid estimation of the derivatives.