Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
Effect of thickness-to-chord ratio on aerodynamics of non-slender delta wing
Date
2019-05-01
Author
Ghazijahani, Mohammad Sharifi
Yavuz, Mehmet Metin
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
209
views
0
downloads
Cite This
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
Suggestions
OpenMETU
Core
Effect of Thickness-to-Chord Ratio on Flow Structure of a Low Swept Delta Wing
Gulsacan, Burak; Sencan, Gizem; Yavuz, Mehmet Metin (American Institute of Aeronautics and Astronautics (AIAA), 2018-12-01)
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 substan...
Effect of ground on aerodynamics and longitudinal static stability of a non-slender delta wing
Koçak, Göktuğ; Yavuz, Mehmet Metin (2022-11-01)
© 2022 Elsevier Masson SASIn this paper, the effect of ground on aerodynamics and longitudinal static stability of a non-slender delta wing with sweep angle of 45 degree and thickness-to-chord ratio (t/c) of 5.9% was characterized at Reynolds number of 9×104 in a low-speed wind tunnel using force and pressure measurements. The measurements were conducted for angles of attack varying between 0≤α≤30 degrees and non-dimensional heights between 3%≤h/c≤107% and height stability of the wing based on aerodynamic c...
Effect of Passive Bleeding on Flow Structure over a Nonslender Delta Wing
Celik, Alper; Cetin, Cenk; Yavuz, Mehmet Metin (2017-08-01)
The effect of passive bleeding on flow structure of a 45 deg swept delta wing is studied in a low-speed wind tunnel using techniques of laser-illuminated smoke visualization, surface-pressure measurements, and particle image velocimetry. Three different bleeding configurations are tested to identify the effectiveness of the control technique compared to a base planform for a broad range of attack angles 6 <= alpha <= 6deg at Reynolds numbers Re=3.5x10(4) and Re=10(5). The results indicate that all bleeding ...
Effect of thickness-to-chord ratio on flow structure of nonslender delta wing
Gülsaçan, Burak; Ghazijahani, Mohammad Sharifi; Şencan, Gizem; Yavuz, Mehmet Metin (2018-11-18)
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 ed...
Transformation of flow structure on a delta wing of moderate sweep angle during pitch-up maneuver
Yavuz, Mehmet Metin (2012-08-01)
The transformation of flow structure on a delta wing of moderate sweep angle is investigated during pitch-up via quantitative imaging in crossflow planes, in relation to qualitative dye visualization. The comparisons are made with the corresponding stationary wing. The effects of different pitch-up maneuver rates and Reynolds numbers on evolution of flow patterns are also addressed. A technique of high-image-density particle image velocimetry is employed for the quantitative analysis. The transformation of ...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
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.