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A study of methods to increase the lift of supersonic airfoils at low speeds... The relatively large increment of lift that can be attributed to the prevention of flow separation at high angles of attack suggests that such boundary layer control could be used to improve controlability and to delay the stall, particularly tip stall, of high speed aircraft with very large sweep back angles

général - core.ac.uk - PDF: thesis.library.caltech.edu

Anomalous shocks on the measured near-field pressure signatures of low-boom wind-tunnel models... Others were attributed to the three-dimension nature of the flow around a lifting model, to inaccuracies in the prediction of the area-ruled lift, or to wing-tip stall effects....

PDF: hdl.handle.net

Transonic aerodynamic loading characteristics of a wing-body-tail combination having 52.5° sweptback wing of aspect ratio 3 with conical wing camber and body indentation for a design mach number [square root of] 2 /... Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall....

PDF: www.hathitrust.org