Abstract This contribution presents an experimental wind tunnel study on the aerodynamics of a 2-Element high-lift airfoil in disturbed inflow conditions. The study contains results from low angle of attack up to stall conditions of the high-lift airfoil. The disturbances used herein are both transient, transversal vortices and a steady, longitudinal vortex, as well as the superposition of both kinds. These vortices are generated upstream of the high-lift airfoil in the wind tunnel test-section by means of two vortex generators. The first part describes fundamental information needed for the disturbance inter­actions afterwards. The aerodynamic behavior of the high-lift airfoil in undisturbed flow will be discussed as well as external, preliminary studies on the generation of the transient, transversal vortices and on their influences regarding the high-lift airfoil. The second part deals with the steady disturbances of the longitudinal vortex on the high-lift airfoil. The longitudinal vortex is basically a wingtip vortex of a finite airfoil placed inside the test-section. By means of a parametric study suitable disturbance cases are identified which generate comparable amplitudes at the high-lift airfoil to the transient, transversal vortices. This study results in two disturbance cases that are evaluated in more detail afterwards. The third part contains the superposition of the steady disturbance cases with the transient, transversal vortices. Results of the pure transient cases and of the steady disturbance cases are resumed and their changes by the superposed disturbances are discussed. The measurement techniques used within the following study are time-averaged and time-resolving static pressure measurements, steady and phase-locked flow field mea­surements and qualitative measurements by surface oilflow visualizations of the high­lift airfoil.weiterlesen