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

Download

index.pdf

Date

2018

Author

Sharifi Ghazijahani, Mohammad

Metadata

Show full item record

Item Usage Stats

258
views

295
downloads

Flow characterization over delta wings have gained attention in recent decades due to their prevailing usage in designs of unmanned air vehicles (UAVs). In literature,only a few studies have reported wing thickness effect on both the aerodynamic performance and detailed flow structure over delta wings. In the present investigation, the effect of thickness-to-chord (t/C) ratio on aerodynamics of a non-slender delta wing with 45 degree sweep angle 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 with t/C ratios varying from 2 % to 15 % are tested at broad range s of angle of attack and Reynolds number. 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 high t/C ratio wings. These results are well supported by the force measurements such that high t/C ratio wings induce higher lift coefficients, CL, at low angles of attack, whereas maximum CL 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, CL/CD, increase in t/C ratio induces remarkable drop in CL/CD values.

Subject Keywords

Airplanes, Leading edges (Aerodynamics)., Flow visualization., Vortex-motion., Drone aircraft.

URI

http://etd.lib.metu.edu.tr/upload/12622914/index.pdf
https://hdl.handle.net/11511/27875

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Effect of thickness-to-chord ratio on flow structure of a low swept delta wing Gülsaçan, Burak; Yavuz, Mehmet Metin; Department of Mechanical Engineering (2017) Low swept delta wings, which are the simplified planforms of Unmanned Air Vehicles (UAVs), Unmanned Combat Air Vehicles (UCAVs) and Micro Air Vehicles (MAVs), have drawn considerable attention in recent years. In order to characterize and improve the operational parameters of these vehicles, the flow physics over low swept delta wings and its control should be well understood. In literature, the effect of thickness-to-chord ratio (t/C) on aerodynamic performance of a delta wing was studied on high and moder...
Control of flow structure on low swept delta wing with staedy leading edge blowing Zharfa, Mohammadreza; Yavuz, Mehmet Metin; Department of Mechanical Engineering (2014) Unmanned Combat Air Vehicles (UCAVs), Unmanned Air Vehicles (UAVs) and Micro Air Vehicles are becoming extremely popular due to introducing many advantages to defense industry and aeronautical field. In line with this, the aerodynamics of these vehicles, which can be represented by simplified planforms, including delta wings, have been of considerable interest in recent years. This interest has stimulated investigation of the flow structure, as well as its control, on delta wings having low and moderate val...
Development and implementation of novel flow control techniques for nonslender delta wings Çelik, Alper; Yavuz, Mehmet Metin; Department of Mechanical Engineering (2017) Understanding and controlling the physical phenomenon behind the aerodynamics of low to moderate swept delta wings has been a challenge for researchers during the last few decades, which is stimulated by their widespread use in unmanned combat air vehicles (UCAVs) and micro air vehicles (MAVs). Although delta wings are capable of generating high lift and stable flight performance at high angle of attack, the problems related to lack of conventional flow control surfaces compel the researchers to explore new...
Effect of wing heating on flow structure of low swept delta wing Şencan, Gizem; Yavuz, Mehmet Metin; Güvenç Yazıcıoğlu, Almıla; Department of Mechanical Engineering (2016) Micro Air Vehicles (MAVs), Unmanned Air Vehicles (UAVs) and Unmanned Combat Air Vehicles (UCAVs), which can be represented by simplified planforms including low swept delta wings, have many advantages in defense industry and aeronautical field. Thus, the aerodynamics of nonslender delta wings including development and application of different flow control techniques have been of considerable interest in recent years. In this study, it is aimed to investigate the effect of heating on the flow structure over...
Control of flow structure on 70° swept delta wing with along-the-core blowing using numerical modeling Küçükyılmaz, İbrahim Can; Yavuz, Mehmet Metin; Department of Mechanical Engineering (2016) In recent years, interest has increased in Unmanned Combat Air Vehicles (UCAVs) and Unmanned Air Vehicles (UAVs), which can be represented by simplified planforms including delta wings. Delta wings experience the formation of two counter-rotating vortices on the leeward side of the planform due to the shear layer separated from the windward side. At sufficiently high angle of attack, these vortices undergo sudden expansion, called vortex breakdown/burst, which is quite detrimental considering the aerodynami...

Citation Formats

M. Sharifi Ghazijahani, “Effect of thickness-to-chord ratio on aerodynamics of non-slender delta wing,” M.S. - Master of Science, Middle East Technical University, 2018.