Abstract This thesis deals with the simulation of streamwise vortices appearing at modern aircraft in high-lift configuration. These vortices strongly impact the aerodynamic behavior close to maximum lift conditions. For this reason, an accurate prediction of the vortex system is essential for the aircraft design process. The investigations cover two different test cases, each featuring a part of the whole characteristic vortex system. The first test case is a generic, swept wing with a slat and a Fowler-flap as high-lift devices. The slat is only deflected in the outer part. At the spanwise end of the slat and the corresponding step of the leading edge, streamwise vortices arise. These vortices proceed along the suction side of the wing influencing the local flow field. Within the second test case, a vortex downstream of a delta-wing is analyzed. The size, the sweep-angle and the angle of attack of the delta-wing were adjusted to create a vortex similar to a nacelle strake vortex. The investigations focus on the ability of different approaches treating turbulence in the simulations to predict the characteristics of the vortices accurately. For both test cases, an eddy viscosity model (Menter-SST), a Reynolds-stress model (JHh-v2 / SSG/LRR-ω) and a hybrid RANS/LES approach were applied. For the second test case, the vortex characteristics were also analyzed with stereo-PIV measurements. It will be shown, that the Menter-SST eddy viscosity model fails to predict the characteristics of the vortices. In contrast, the results of the Reynolds-stress models are in good agreement with the scale-resolving simulation for the first test case and with the stereo-PIV measurements for the second test case. However, these models strongly underpredict the turbulent values. Here, the hybrid RANS/LES approach shows promising results for the second test case.weiterlesen