PARALLEL NUMERICAL COMPUTATION OF DISTRIBUTION OF PRESURE PAST AN OSCILATING AIRFOIL NACA0015

The article is devoted to 2D parallel numerical computation of pressure on the surface of an elastically supported airfoil self-oscillating due to interaction with the airflow. Movement of airfoil is described by translation and rotation, identified from experimental data. A new boundary condition for the 2DOF motion of the airfoil was implemented in OpenFoam, an open-source software package based on finite volume method. The results of numerical simulation (distribution of pressure on the surface of airfoil) are compared with experimental data measured in a wind tunnel, where a physical model of NACA0015 airfoil was mounted and tuned to exhibit the flutter instability. The experimental results were obtained previously in the Institute of Thermomechanics by interferographic measurement in a subsonic wind tunnel.