Canpolat, C.Yayla, S.Sahin, B.Akilli, H.2025-05-102025-05-1020170893-13211943-552510.1061/(ASCE)AS.1943-5525.00007662-s2.0-85020449293https://doi.org/10.1061/(ASCE)AS.1943-5525.0000766https://hdl.handle.net/20.500.14720/5782Sahin, Besir/0000-0003-0671-0890The objective of this work is to reveal the significance of a trailing-edge attachment on the flow structure over a generic nonslender delta wing using the dye visualization technique on the top-view plane. Instantaneous images are acquired by stereoscopic particle image velocimetry (stereo-PIV) to calculate time-averaged flow data, with angle of attack, a, and yaw angle,., are varied within 7 degrees <= alpha <= 17 degrees and 0 degrees <= theta <= 15 degrees, respectively. It is shown that time-mean locations of vortex breakdown for the nonslender delta and lambda wings occur in the field close to the wings. As a result, no remarkable alteration is observed for the spatial locations of the vortex breakdown. The experiments also show that the., which is a crucial parameter, alters the flow structure over the nonslender delta wing substantially compared with the lambda wing. It is concluded that the trailing-edge attachment plays vital role when. becomes effective. (C) 2017 American Society of Civil Engineers.eninfo:eu-repo/semantics/closedAccessAngle Of AttackGeneric Delta WingParticle Image VelocimetryWing PlanformYaw AngleArticle305Q2Q3WOS:000408670600044