Performance Characteristics of the NREL S826 Airfoil - An assessment of Re-Independency and effect of inflow turbulence
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Lift- and drag measurements on an NREL S826 airfoil were performed experimentally in NTNU s low-speed wind tunnel. Reynolds number effects were investigated in the range Re = 0.7 × 105 6.0 × 105 at angles of attack between -16.5⁰ and 28.5⁰. A turbulence-generating grid was placed upstream to investigate the effect of high turbulence inflow on the airfoil performance. The pressure distribution was measured using 32 pressure taps along the wing surface. Drag coefficients were obtained by integration of the momentum loss in the wake. Lift coefficients were measured by direct force measurements (force gauge).With low turbulence inflow conditions no significant Reynolds number effects were observed. The maximum lift coefficient and corresponding angle of attack were found to be slightly higher than a reference experiment performed on the same airfoil . Higher turbulence levels in the inflow increased the maximum lift and reduce drag as it delays separation on the upper surface on the airfoil.