Computation of Unsteady Flow over a Plunging Aerofoil Using an Implicit Reynolds Averaged Navier-Stokes Solver

Unsteady Reynolds-Averaged Navier-Stokes (RANS) computations are presented for subsonic and transonic flow past a plunging NACA 64A010 aerofoil. The RANS solver used for obtaining the time-accurate solutions is based on an implicit dual time stepping scheme with finite volume nodal point spatial discretization. Results for the subsonic and transonic cases compare well with the experimental data, thus demonstrating the capability of the solver to provide useful unsteady pressure data for aero-elastic analysis