The LS(1)-0417MOD Airfoil Aerodynamic Flow Characteristcs with the Application of Vortex Generators

Abstract

The second phase of testing using the LS(1)-0417MOD airfoil model was completed in The Ohio State University’s 3x5 wind tunnel for conditions including a clean (baseline) surface, leading edge grit roughness and vortex generators. The tests were conducted in both twodimensional and three-dimensional model configurations and for steady state and unsteady flow conditions. Local lift, moment and pressure drag were obtained from six spanwise pressure distributions. The results showed that the application of the grit roughness reduces the maximum lift coefficients in all configurations. A large increase in the maximum lift coefficient was observed with the application of the vortex generators in 3D steady state flow for all the spanwise stations. For the 3D unsteady flow, the maximum lift coefficients were always higher than those for steady state, even with the application of the vortex generators. The smallest hysteresis loops were found at the tip spanwise station. The application of specific vortex generators eliminated the hysteresis loops and increased the maximum lift coefficient significantly in the 3D model configuration, especially in the wall station.