WITHDRAWN: WIND TUNNEL INVESTIGATION OF WAKE CHARACTERISTICS OF A WING WITH WINGLETS

Aircraft performance such as range and endurance is highly dependent on induced and vortex drag. There is a close relationship between wake structure and aerodynamic performance. In the present paper the velocity field behind the model of wing with winglet is studied. The methodology and equipment for the study in low speed wind tunnel ULAK – 1 are presented. The pressure field is obtained using a five-hole pressure probe which is positioned in a cross plane at 300 mm behind the wing trailing edge. Acquired experimental data are used to calculate cross flow velocity and vorticity fields at an angle of attack of 6 degrees - around maximum lift to drag ratio. The results are compared to the data of the model with planar wing. During the subsequent processing coefficients of lift and induced drag can be obtained.