後退翼上の三次元境界層の遷移

概要

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It is well known that the viscous drag increases for swept wings because of skewed turbulent boundary layers. In the present paper, in order to investigate the transition mechanism of boundary layers on swept wings, wind tunnel experiments and numerical computations of flow are performed. Experiments are carried out by using the closed-circuit wind tunnel at Tokai University. A swept wing model which can be set for variable swept angle at a root is mounted vertically in the 1.5m×1.0m test section. Measurements are done by a two-dimensional hot wire anemometer with computer controlled three-dimensional traverse system and data processing system. Computations are done by using the fluid analysis software FLUENT. Measuring velocities insideboundary layers at various swept angles, the relations between swept angles and transitions are investigated. As a result, the negative peak of correlation function R gives an indication of turbulent transition.
東海大学の論文