Effect of thickness-to-chord ratio on flow structure of nonslender delta wing

Date

2018-11-18

Author

Gülsaçan, Burak
Ghazijahani, Mohammad Sharifi
Şencan, Gizem
Yavuz, Mehmet Metin

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The effects of thickness-to-chord (t/C) ratio on flow structures of nonslender delta wings with sweep angles of 35 and 45 degrees are characterized in a low-speed wind tunnel using velocity, pressure, and force measurements. The delta wings with t/C ratios varying from 2 % to 19 % are tested at broad ranges of attack angles and Reynolds numbers. The results indicate that the effect of t/C ratio on flow structure is quite substantial. Considering the low angles of attack where the wings experience leading edge vortex structure, the strength of the vortex structure increases as the t/C ratio increases. However, the wing with lowest t/C ratio has pronounced surface separation at significantly higher angle of attack compared to the wing with highest t/C ratio, which indicates that lowest t/C ratio wing might be more resistive to the stall condition. These results are well supported by the force measurements such that high t/C ratio induces higher lift coefficient, CL, at low attack angles, whereas maximum CL values that can be reached are significantly higher and appears at significantly higher angle of attack for low t/C ratio wings. Considering the CL/CD ratio, increase in t/C ratio induces remarkable drop in CL/CD values.

URI

https://hdl.handle.net/11511/76141
https://meetings.aps.org/Meeting/DFD18/Session/G16.6

Conference Name

71st Annual Meeting of the APS Division of Fluid Dynamics, (November 18–20, 2018)

Collections

Department of Mechanical Engineering, Conference / Seminar

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Citation Formats

B. Gülsaçan, M. S. Ghazijahani, G. Şencan, and M. M. Yavuz, “Effect of thickness-to-chord ratio on flow structure of nonslender delta wing,” presented at the 71st Annual Meeting of the APS Division of Fluid Dynamics, (November 18–20, 2018), Atlanta, Georgia, USA, 2018, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/76141.