Effect of wing heating on flow structure of low swept delta wing

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2016
Şencan, Gizem
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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 a 35° swept delta wing. By applying uniform heat flux from the suction side of the wing, which represents the top surface of the wing, the flow structure has been investigated using Particle Image Velocimetry (PIV) techniques for the cross flow plane at the chordwise distance of {u1D465} {u1D436} ⁄ = 0.6 in a low speed wind tunnel. The velocity measurements are conducted for the attack angles of {u1D6FC} = 4°,7°,10°,13° at Reynolds numbers of {u1D445}{u1D452} = 3000, {u1D445}{u1D452} = 8000 and {u1D445}{u1D452} = 10000. In this study, it is aimed to investigate the effect of heating on the flow structure over a 35° swept delta wing. By applying uniform heat flux from the suction side of the wing, which represents the top surface of the wing, the flow structure has been investigated using Particle Image Velocimetry (PIV) techniques for the cross flow plane at the chordwise distance of {u1D465} {u1D436} ⁄ = 0.6 in a low speed wind tunnel. The velocity measurements are conducted for the attack angles of {u1D6FC} = 4°,7°,10°,13° at Reynolds numbers of {u1D445}{u1D452} = 3000, {u1D445}{u1D452} = 8000 and {u1D445}{u1D452} = 10000. The results indicate that applying uniform heat flux from the suction side of the wing planform does not produce considerable variation on the overall flow pattern within the operational ranges tested in the current study. The effects are limited to low Reynolds number cases with indicating different behaviors for vortex dominated and pre-stall regimes such that for the attack angles {u1D6FC} = 4° and {u1D6FC} = 7° the wing heating causes drop in vorticity levels with shifting the concentrations toward the center of the planform, whereas at {u1D6FC} = 10° the movement of vorticity concentrations toward the leading edge of the planform with increase in levels is witnessed. Further studies are needed to extend the operational ranges and to draw concrete conclusions regarding the effect of heating on flow structure of low swept delta wing.
Airplanes, Airplanes, Stalling (Aerodynamics)., Fluid dynamics.
http://etd.lib.metu.edu.tr/upload/12620664/index.pdf
https://hdl.handle.net/11511/26199
Graduate School of Natural and Applied Sciences, Thesis

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Citation Formats
G. Şencan, “Effect of wing heating on flow structure of low swept delta wing,” M.S. - Master of Science, Middle East Technical University, 2016.
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