Numerical Investigation of the Flow Around Different Slat Tracks on a Swept High Lift Wing Segment

Kurzfassung

A numerical investigation of a high lift segment using an unstructured RANS method shows, that a slat track can have a significant influence on the overall aerodynamic properties. Two track types are considered, one which is representative of a wind tunnel model, and a second one derived from an aircraft track. The major differences are the larger cross-section area of the model track, and the intersection with the fixed wing. The high lift devices are positioned in a landing setting. The onflow conditions refer to wind tunnel conditions. Periodic lateral boundary conditions are applied. Compared to a reference high lift wing segment without track, a 10% increase in lift and a 20% increase in drag is being computed for the model track. For the aircraft track only a minor lift change is found, but also a 20% drag increase. Based on the outcome of the present investigations, the major impact of the lift is caused by the downstream shift of the stagnation line in the vicinity of the junction of the model track and the fixed wing.