Numerical Analysis of 2D Subsonic Flow over Oscillating Airfoil at Incidence

The compressible flow over NACA64a0l0 airfoil has been numerically simulated using an unsteady compressible two- dimensional Navier-Stokes solver using the dynamic mesh technique. The OpenFOAM toolbox was used for this purpose, and increment of the lift-drag ratio has been obtained at the free-stream Mach number of 0.569 and 2 angle of attack. The Pimple algorithm was used for the discretiyation of the basic equations based on the control- volutne method, and the K-to SST model for turbulencemodeling. First. the results of compressible flow simulation around the fixed NACA64a0l0 airfoil were validated with the existing experimental data. Then the effects of plunging amplitude and oscillating frequency on the aerodynamic loads have been investigated. The results showed that when the plunging amplitude increases from 0 to 0.2, the lift coefficient at the Mach number of 0.569 experiences 2% and 5% enhancement with a slight decrease of the drag force.

کلیدواژه ها:

airfoil ، compressible flow ، subsonic regime ، dynamic mesh ، OpenFOAM