後退翼上三次元乱流境界層のモデル予測

概要

論文の詳細を見る
A full second-moment closure which was previously shown to reproduce a weakly three-dimensional boundary layer as well as various two-dimensional flows is employed to calculate the boundary layer on a swept wing. The numerical solutions are extensively compared with the experiments by van den Berg et al. The agreement is generally reasonable. Particular attention is given to the effect of retaining the terms with 'secondary' velocity gradients in the model equations. It is shown that the decrease in the structure parameter (the shear-stress/energy ratio) is attributable, at least partially, to the 'secondary' terms. However, the large lag between the shear stress direction and the velocity gradient direction is not well reproduced. A revision of the redistribution terms is needed to capture this behavior, as suggested by several authors.
1991-02-25