Investigation of the hydrogen production potential of the H-Darrieus turbines combined with various wind-lens

Tanürün, Himmet Erdi; Acır, Adem

doi:10.1016/j.ijhydene.2022.04.196

Cited by 7 publications

(1 citation statement)

References 62 publications

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“…The detailed analysis of Humpback flippers revealed that round protuberance shapes at its flipper is unique than other aerobatic animals. Moreover, over the last few years numerous studies has been carried out to control flow in the subsonic [3][4][5][6][7][8][9][10][11][12][13] and the transonic flow regimes [14][15][16][17]. The deployment of tubercle in various rotating fluid machinery application such as propeller [18,19], wind turbines [18,[20][21][22][23][24][25][26][27][28][29][30] and on the tidal turbine [31][32][33] to improve their aerodynamic performance, by controlling dynamic stall is gaining research attention over last decade.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Performance Enhancement of Low Aspect Ratio Military Drone Aircraft Wing through Employing Leading Edge Tubercles

2024

IJFMR

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Present study aim to improve the aerodynamic performance of low Aspect Ratio (AR) military drone aircraft wing, through employing leading edge tubercle. For that purpose two wing model were design one with smooth leading edge and second with tubercle leading edge. The wing models were developed by using NACA0012 airfoil profile, whereas tubercles of amplitude 5% of chord (c) and wavelength of 11% of c is employed. The numerical simulation as performed at chord based Reynolds number of 140000 in pre-stall and post stall regime. The computational fluid dynamic simulation is performed at different angle of attack ranging from 0 degree to 25 degree with the interval of 5 degree. Computational Fluid Dynamics (CFD) results reveal that tubercle at the leading edge of the low AR wing has favorable effect on the wing performance. Aerodynamic performance of both smooth leading edge and tubercle leading edge wing is similar up to 15o angle of attack, whereas at 20 degree and 25 degree significant improvement in Lift-to-Drag L/D ratio is observed. It is estimated that at maximum increment of 53% in lift coefficient ii achieved at 25 degree angle of attack for as compared to smooth LE wing model. Moreover, maximum 20.5% decrease in drag coefficient is estimated in case of tubercle leading edge as compared to baseline model at 20 degree angle of attack. The critical observation of field around the tubercle leading edge wing is found that tubercles restrict flow separation through generation of low strength vortices; these vortices enhance momentum exchange within the boundary layer.

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