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- W4377230310 abstract "True situation for inviscid irrotational fluid flow when sharp or rounded trailing edged Aerofoil is submerged in high Reynold number fluid flow results to either lifting (due to momentum), dragging (due to viscosity) or both. This is predominant in lifting and thrusting aircraft with the use of wings. This article has attempted to investigate the velocity distribution on thin ellipsoidal Aerofoil geometry of aircraft wing using Surface Vorticity Method. A 2 Dimensional CAD (Computer Aided Design) of customized Aerofoil (M=3.0%, P=50.0%, T=20.0%) was designed and simulated using Aerofoil Tools. Vorticity equations were generated in addition to the use of coupling parameters to generate Surface Vorticity equations. The numerical models were then simulated with inbuilt parameters on turbulence (realizable) k- <tex xmlns:mml=http://www.w3.org/1998/Math/MathML xmlns:xlink=http://www.w3.org/1999/xlink>$varepsilon$</tex> physics interface on normal flow with reference inlet velocity, <tex xmlns:mml=http://www.w3.org/1998/Math/MathML xmlns:xlink=http://www.w3.org/1999/xlink>$U_{o} =0.1x10^{-10} m/s$</tex> , using COMSOL Multiphysics. The simulation was run for 86400 s. (24 hrs.) and results analyzed at interval of 60 s. The overall velocity drop of <tex xmlns:mml=http://www.w3.org/1998/Math/MathML xmlns:xlink=http://www.w3.org/1999/xlink>$2.03times 10^{-13} m/s$</tex> was experienced on the 86400th s at the attack and tip-of-wake of Aerofoil. The overall highest velocity at the boundary layers was <tex xmlns:mml=http://www.w3.org/1998/Math/MathML xmlns:xlink=http://www.w3.org/1999/xlink>$7.37times 10^{-20} m/s$</tex> at the first 60th. These shows decreasing trend in velocity at the boundary of attach and wake and increasing trend in velocity at the boundary layer region which fades-out towards free stream region of the Aerofoil." @default.
- W4377230310 created "2023-05-23" @default.
- W4377230310 creator A5065657550 @default.
- W4377230310 date "2023-04-05" @default.
- W4377230310 modified "2023-09-26" @default.
- W4377230310 title "Towards Numerical Investigation of Velocity Variation on Thin Ellipsoidal Aerofoil (NACA 3520) Using Surface Vorticity Method" @default.
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- W4377230310 doi "https://doi.org/10.1109/seb-sdg57117.2023.10124382" @default.
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