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Asymptotic Modeling of Subsonic Potential Laminar Viscous Flow Over a NACA Airfoil: Simulation and Experimentation Validation


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DOI: https://doi.org/10.15866/ireme.v16i9.22546

Abstract


The aim of this paper is to solve the singular perturbation equation modeling potential laminar viscous flow in compressible subsonic regime at high Reynolds number to count for the shock wave boundary layer interaction. By means of singular perturbations methods, two distinguished models are defined and solved, i.e. the boundary layer viscous flow model and the outer inviscid flow model. The obtained theoretical solution compares well with both the results of a NACA 43013 airfoil produced by numerical simulation conducted using ANSYS fluent and AF300 wind tunnel experiments. At low angle of incidence and attached flow, validation of the theoretical results, compared to numerical simulations, shows good agreement in case of laminar boundary layer flow and in the presence of shockwaves. The mean relative error is under 6%. Meanwhile, the model becomes less accurate, when compared with experimental results, as the flow becomes turbulent towards the trailing edge of the airfoil. The mean relative error is 10%.
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Keywords


Subsonic Compressible Flow; Potential Viscous Flow; Laminar Flow; Perturbation Methods; Asymptotic Methods; Wind Tunnel Experimentation

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References


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