Effect of thickness-to-chord ratio on aerodynamics of non-slender delta wing

Date

2019-05-01

Author

Ghazijahani, Mohammad Sharifi
Yavuz, Mehmet Metin

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The effect of thickness-to-chord (t/C) ratio on aerodynamics of a non-slender delta wing with sweep angle of 45 degree is characterized in a low-speed wind tunnel using laser illuminated smoke visualization, surface pressure measurements, particle image velocimetry, and force measurements. The delta wings of t/C ratios varying from 2% to 15% with 45 degree windward beveled leading edges are tested. 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, low t/C ratio wings have pronounced surface separations at higher angle of attack compared to the wings with high t/C ratios. These results are well supported by the force measurements such that high t/C ratio wings induce higher lift coefficients, C-L, at low angles of attack, whereas maximum C-L values are higher and appear at higher angle of attack for low t/C ratio wings. This indicates that low t/C ratio wings are more resistive to the stall condition. Considering the lift-to-drag ratio, C-L/C-D, increase in t/C ratio induces remarkable drop in C-L/C-D values. (C) 2019 Elsevier Masson SAS. All rights reserved.

Subject Keywords

Near-surface topology, Flow structure, Vortex flows

URI

https://hdl.handle.net/11511/32935

Journal

AEROSPACE SCIENCE AND TECHNOLOGY

DOI

https://doi.org/10.1016/j.ast.2019.03.033

Collections

Department of Mechanical Engineering, Article

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Citation Formats

M. S. Ghazijahani and M. M. Yavuz, “Effect of thickness-to-chord ratio on aerodynamics of non-slender delta wing,” AEROSPACE SCIENCE AND TECHNOLOGY, pp. 298–307, 2019, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/32935.