Urban wind simulations are essential for assessing pedestrian comfort, pollutant dispersion, and microclimate design, yet high-fidelity CFD remains computationally expensive. This thesis investigates the potential of a Swin-Transformer-based surrogate model to approximate steady-state 2D results for 100 m × 100 m tiles under a single inflow direction. A dataset of 690 urban tiles was extracted from the 3DBAG and simulated in Ansys Fluent at 0.5 m resolution across five inflow speeds (5–15 m/s) and five types of building layouts. Velocity fields were rasterized to 1 m grids. The surrogate architecture preserves the original Swin backbone, evaluated with three loss variants: original RMSE, buffer weighting, and a divergence penalty. Encoding wind as xy-component consistently outperformed magnitude-only training. Errors scaled linearly with inflow speed and were highest in Mixed and Attached urban forms. Architectural resolution was the dominant factor influencing accuracy since it introduced visible artifacts, while the buffer and divergence losses offered only marginal improvements. Limitations remain near building facades, where sharp gradients are smoothed by the patch-based architecture. Nonetheless, the surrogate offers potential for rapid wind flow estimation suitable for early-stage design or preliminary analysis.

Strut-braced wings have recently garnered renewed interest in the aerospace industry due to their potential to improve aerodynamic efficiency and reduce structural weight. However, current Computational Fluid Dynamics (CFD) software tools face significant challenges in accurately predicting the unsteady flow phenomena associated with such designs, particularly in junction flow dynamics. This thesis aims to validate the capabilities of a Lattice Boltzmann Method (LBM) solver in predicting both the aerodynamic and aeroacoustic features of a model strut-braced wing. To achieve this, a series of wind tunnel tests were conducted to provide experimental data for comparison with the CFD results. Results showed good agreement between numerical and experimental steady measurements. The numerical solver could predict correct surface pressure distributions and a correct pressure coefficient was attainable for an adjusted angle of attack. Furthermore, the numerical method matched wake rake results to a high degree. However, the CFD transitional model was less sensitive to the transition strips, incorrectly assuming untripped flow at the wing surface when in the wind tunnel, the trips successfully transitioned the boundary layer.
The numerical model struggled to capture the unsteady phenomena due to the junction flow at the strut wing intersection. Unsteady pressure measurements showed that the LBM solver overpredicted surface pressure fluctuations near the junction region, affecting the accuracy of the acoustic analogy employed by the CFD software and, ultimately, misrepresenting the junction as the primary acoustic noise source. As such, the solver in question struggles to accurately predict the noise of a strut-braced wing. Moreover, further investigation must be done to improve the wind tunnel anechoic performance, as the tunnel diffusor and test section were identified as the dominant noise sources, thus hindering the analysis.