Investigation of engine jet/wing-tip vortex interference

The wing-tip vortex of a rectangular wing half-model with a model engine is studied experimentally and numerically. The airfoil has a supercritical BAC 3-11/RES/30/21 geometry with a chord length of c=150 mm. The investigations include three different spanwise positions of the engine and two jet velocities with a constant free stream velocity of u∞=27 m/s yielding Rec=2.8×105. The numerical simulation is divided into two parts. First the flow around the airfoil is calculated. In a second step the data is taken as an input to calculate the wake downstream of the trailing edge. Experiments include 2C- and 3C-PIV-measurements for the velocity distribution of the jet and the wing-tip vortices. The experimental and numerical results show the significance of the streamwise velocity component for the analysis of the jet/wing-tip vortex interaction.