Colloquium: Mustafa Sabri Güverte (FPT)

The thesis aims to experimentally validate the capabilities of a Lattice Boltzmann Method solver in predicting the flow features of a strut-braced wing. Results showed good agreement between numerical and experimental steady measurements. However, the CFD transitional model was less sensitive to the transition strips, incorrectly assuming untripped flow at the wing surface. The numerical model struggled to capture the unsteady phenomena due to the junction flow at the junction region. Unsteady pressure measurements showed that the LBM solver overpredicted surface pressure fluctuations near the junction region, affecting the accuracy of the acoustic analogy, ultimately, misrepresenting the junction as the primary acoustic noise source. As such, the solver 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.

Supervisor: Frits de Prenter