Numerical Computation of Unsteady Compressible Flow past a Plunging Aerofoil


Computational and Theoretical Fluid Dynamics Division, Council of Scientific and Industrial Research, National Aerospace Laboratories, Bangalore – 560017, India


Unsteady Reynolds-averaged Navier-Stokes (RANS) computations are presented for subsonic and transonic flow past a plunging NACA 64A010 aerofoil. The Implicit RANS solver used for obtaining the time-accurate solution is based on finite volume nodal point spatial discretization scheme with dual time stepping. 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 aeroelastic analysis.