Mean velocity characteristics in the asymmetric far wake behind GAW (2) airfoil

ABSTRACT The two-dimensional turbulent asymmetric far wake behind a General Aviation Wing-2 cambered airfoil section is studied at a subsonic speed at zero angle of attack. The near wake flow is the region of the wake flow close to the trailing edge of the airfoil, which is dictated by the interaction of the on-coming turbulent boundary layers. Far wake is the region of the wake flow which is at a large distance from the training edge. In the current research work, mean velocity measurements have been made and analysed in the far wake, where initial asymmetric wake has become symmetric with respect to the minimum velocity line. Minimum mean velocity, wake half thickness, momentum thickness and shape parameter based on the streamwise component of mean velocity development in the turbulent asymmetric far wake are presented here. Governing equations have been solved with appropriate boundary conditions in the far wake. Self-similarity solutions have been obtained for the governing equations for mean velocity distributions. Results of self-similarity analysis have been compared with experimental data. The focus on far wake flow behaviour with mean velocity profile asymmetry, is motivated by their importance of the high-lift systems utilized in the commercial transport airplane designs. Keywords: Far wake, GAW(2) airfoil, mean velocity, momentum thickness, drag coefficient.