Flow structures in end-view plane of slender delta wing
1 Department of Mechanical Engineering, Faculty of Engineering and Architecture, Cukurova University, 01330, Adana / Turkey
2 Departments of Aerospace Engineering, Faculty of Aeronautics and Aerospace, Gaziantep University, 27310, Gaziantep / Turkey
* Corresponding author: email@example.com
Published online: 12 May 2017
Present investigation focuses on unsteady flow structures in end-view planes at the trailing edge of delta wing, X/C=1.0, where consequences of vortex bursting and stall phenomena vary according to angles of attack over the range of 25° ≤ α ≤ 35° and yaw angles, β over the range of 0° ≤ β ≤ 20°. Basic features of counter rotating vortices in end-view planes of delta win with 70° sweep angle, Λ are examined both qualitatively and quantitatively using Rhodamine dye and the PIV system. In the light of present experiments it is seen that with increasing yaw angle, β symmetrical flow structure is disrupted continuously. Dispersed wind-ward side leading edge vortices cover a large part of flow domain, on the other hand, lee-ward side leading edge vortices cover only a small portion of flow domain.
© The Authors, published by EDP Sciences, 2017
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