2次元翼型失速限界のCFD予測

概要

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Two-dimensional Navier-Stokes simulations have been performed for three types of flows at stall conditions about NACA633-018, NACA631-012 and NACA64A-006 airfoils. The Baldwin-Lomax algebraic eddy-viscosity model was applied in three different manners. First, a fully turbulent flow was assumed. Second, a transition point from laminar to turbulent was set manually. Third, the Degani-Schiff modification was applied. The fully turbulent computations predicted maximum lift coefficients much higher than experiment in all the cases, while the computations agreed well with experiment when specifying transition points properly. The computations with the Degani-Schiff modification predicted the stall angle close to experiment, but showed different behaviors at post-stall conditions. It is important to capture a laminar separation bubble at the leading-edge for predicting stall angles and post-stall behaviors correctly.
社団法人日本航空宇宙学会の論文
2002-02-05