Effect of Thickness-to-Chord Ratio on Flow Structure of a Low Swept Delta Wing

Date

2018-12-01

Author

Gulsacan, Burak
Sencan, Gizem
Yavuz, Mehmet Metin

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The effect of thickness-to-chord (t/C) ratio on flow structure of a delta wing with sweep angle of 35 deg is characterized in a low-speed wind tunnel using laser-illuminated smoke visualization, particle image velocimetry, and surface pressure measurements. Four different t/C ratios varying from 4.75 to 19% are tested at angles of attack, 4, 6, 8, and 10 deg, for Reynolds numbers Re =1 x 10(4) and 3.5 x 10(4). The results indicate that the effect of thicknessto-chord ratio on flow structure is quite substantial, such that, as the wing thickness increases, the flow structure transforms from leading edge vortex to three-dimensional separated flow regime. The wing with lowest t/C ratio of 4.75% has pronounced surface separation at significantly higher angle of attack compared with the wing with highest t/C ratio, which indicates that lowest t/C ratio wing might be more resistive to the stall condition. However, considering the low angles of attack where all wings experience leading edge vortex structure, the strength of the vortex structure increases as the t/C ratio increases, which might suggest a better vortex-induced lift performance with high t/C ratio wing at low angles of attack.

Subject Keywords

Aerospace Engineering

URI

https://hdl.handle.net/11511/38143

Journal

AIAA JOURNAL

DOI

https://doi.org/10.2514/1.j057083

Collections

Department of Mechanical Engineering, Article

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Citation Formats

B. Gulsacan, G. Sencan, and M. M. Yavuz, “Effect of Thickness-to-Chord Ratio on Flow Structure of a Low Swept Delta Wing,” AIAA JOURNAL, pp. 4657–4668, 2018, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/38143.