Santiago-Hernández, Jeffrey

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Boundary layers affected by pressure fields of adjacent compressor blades: A numerical approach
(2018-05) Santiago-Hernández, Jeffrey; Torres-Nieves, Sheilla; College of Engineering; Gutierrez, Jorge Gustavo; Araya, Guillermo; Pérez, Nestor; Department of Mechanical Engineering; Canals, Miguel
Reynolds Average Navier Stoke (RANS) models and Large Eddy Simulation (LES) model, were used to simulate a two NACA 65-410 airfoil compressor cascade using an overset mesh. For mesh validation, comparison of pressure, lift and drag coefficients with experimental data were performed at different angles of attack (AoA) for a single NREL S-826 airfoil. Results of the NACA 65-410 compressor cascade at an AoA of 0 and 7 deg with turbulent intensities of 1% and 6 % show that LES can capture, with better accuracy than RANS models, the effects produced by the adjacent airfoil in the boundary layer velocities and fluctuations. Also, LES captured flow separation at 74% of the chord (c), confirmed by mean velocity profiles and skin friction coefficient (Cf) calculations. Locations of transition from laminar to turbulent flow were approximated using the Cf. Values were between 41.8% and 43.7% c, in agreement with literature.