关键词: 风洞侧壁干扰, Navier-Stokes方程, 有限体积法, 拐角区流动, 机翼半模

Abstract:

A cell centered finite volume scheme that applies a multistage time stepping scheme in conjunction with steady state acceleration techniques is used to solve the integral form of mass averaged three dimensional Navier Stokes equations for flows over a swept NACA0012 wing and a thin low aspect ratio wing mounted in a wind tunnel. Attention is given to various aspects of computation of viscous side wall effects on the flow around a wing. These include the extension of the Baldwin Lomax turbulence model to compute flows in junctures and the treatment of the boundaries of the computational domain. Results for different wings are compared to free air Navier Stokes solutions and to experimental data. It is shown that the pressure distributions at 3 spanwise locations compare well with the experimental data, many of the flow features typical of junction flow have been predicted and the effects of the viscous side wall on flow pattern over the wing surface, particularly in the vicinity of the wing/wall juncture, are significant.

Key words: side wall interference, Navier Stokes equations, finite volume method, juncture flow, half span wing model