Numerical investigation of flutter stability for the flat cascade of airfoils

Numerical simulation of the airflow around the flat cascade of vibrating airfoils has been made. Calculations are performed using ANSYS CFX. Blade surface displacements are taken into account by applying a moving mesh that is being deformed at each time step. Numerical and experimental cascade results are compared. The calculated results are used to determine blade flutter stability. Neutral pitch axis position is obtained.