Abstract:
The author's treatment of the Mangler and Smith vortex-sheet model of leading-edge separation is extended to the calculation of steady conical flow past a yawed slender delta wing. Introducing yaw destroys the symmetry property inherent in the unyawed problem necessitating that the two leading-edge vortex sheets be treated as independent but mutually interacting singularity distributions in the cross-flow plane of the slenderbody theory. From the calculations, predictions are obtained of the variation of the principal quantitative flow characteristics -- including the two primary vortex core positions and the wing rolling-moment coefficient -- with the incidence and yaw parameters. Comparison of these predictions with experimental data is reasonable qualitatively but only fair quantitatively, the discrepancies being attributed to the neglect, in the flow model, of the effects of the secondary separation system on the windward side of the wing. The range of the present calculations is to some extent limited by failure of the solution technique at lower values of the incidence parameter.
