Control of flow structure on low swept delta wing using unsteady leading edge blowing

Download

index.pdf

Date

2016

Author

Çetin, Cenk

Metadata

Show full item record

Item Usage Stats

209
views

95
downloads

There is an increasing interest in recent years in the aerodynamics of low swept delta wings, which can be originated from simplified planforms of Unmanned Air Vehicles (UAV), Unmanned Combat Air Vehicles (UCAV) and Micro Air Vehicles (MAV). In order to determine and to extend the operational boundaries of these vehicles with particular interest in delaying stall, complex flow structure of low swept wings and its control needs to be understood. Among different flow control strategies, blowing through different locations of the wing has been commonly used due to its high effectiveness. Steady and unsteady blowing with different configurations in terms of excitation pattern at different injection rates needs to be studied thoroughly. In the current study, it is aimed to control the flow structure of a low swept delta wing with sweep angle of Λ=45o using unsteady blowing through leading edges. Experiments are conducted in low speed wind tunnel. First, the unsteady blowing test set-up, which is able to provide a broad range of periodic excitation frequencies and injection rates, is built and characterized using Hot Wire Anemometry. Then, the flow structure on the wing is quantified using surface pressure measurements and Particle Image Velocimetry (PIV) technique for the attack angles varying from 7 to 20 degrees at Reynolds number of Re=35000. Different periodic excitation frequencies, varying from 2 Hz to 24 Hz, at fix momentum coefficient are tested and compared with the steady injection cases. The results indicate that unsteady blowing through leading edges of the planform is quite effective for the eradication of stall.

Subject Keywords

Vortex flaps., Vortex-motion., Flaps (Airplanes)., Airplanes

URI

http://etd.lib.metu.edu.tr/upload/12620131/index.pdf
https://hdl.handle.net/11511/25738

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

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...
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...
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...
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...

Citation Formats

C. Çetin, “Control of flow structure on low swept delta wing using unsteady leading edge blowing,” M.S. - Master of Science, Middle East Technical University, 2016.