Work

Numerical study of the lift coefficient for different angles of attack

Year: 2025

Type: dissertation

Abstract: This study presents a numerical analysis of the flow over the symmetric NACA0012 airfoil, focusing on boundary layer separation under different angles of attack (a) and Reynolds numbers (Re). Using the OpenFOAM® software, with two-dimensional meshes generated via the Classy Blocks Python library, four simulations were conducted with the simpleFoam solver, covering both laminar and turbulent regimes. The analysis showed that increasing a raises the lift coefficient (C) up to the stall region, with the transition to turbulence acting as a stabilizing factor for the boundary layer. The numerical results confirm classical aerodynamic theory, highlighting recirculation zones, pressure gradient variations, and the influence of turbulence modeling on airfoil performance.

Source: Institutional Repository of the Federal Technological University of Paraná (RIUT) (Federal University of Technology – Paraná)

Author: Franciscon, Matheus Basseto

Language: Portuguese

Topic: Computational Fluid Dynamics and Aerodynamics

Subfield: Computational Mechanics

Field: Engineering

Domain: Physical Sciences

Open Access status: green

OpenAlex ID: W7155458224

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