F122 Simulation of a Flow around a Subsonic Airfoil with a Circulation Boundary Condition

概要

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In the present paper, a simulation of a subsonic flow around airfoil NACA0012 is attacked. Computations are done at angles of attack 8° to 18° and at the Reynolds number of 10^6 based on the chord length. In these computations, the incompressible Navier-Stokes equations are solved by the multi-directional finite-difference method with using an O-type grid system. For high Reynolds number flow, no explicit turbulence models are employed, but a third-order upwind scheme is adopted. On the far boundary, circulation is controlled consistently, and a periodic boundary condition is used in the spanwise direction. Results show that circulation control on the far boundary has effect on the flow field, especially, it increases the value of Cl at low angles of attack.
2004-08-09