Numerical Investigation of Shock-Buffet Phenomena 2-D

Kurzfassung

This report is a summary of the numerical study dealing with the influence of different modelling parameters on numerical simulation of 2-D unsteady transonic flows. The focus of research lies on simulations of self-sustained shock oscillations (shock-buffet) since this mechanism can play an important role in the aeroelastic behaviour of modern large-wing-span aircrafts. Three diffrent airfoils (NACA 64A010, NACA 0012 and NLR 7301) are investigated by using the DLR-Tau code, a time-accurate hybrid RANS flow solver. The main objectives of the simulations are: (i) to analyse the role of the profile geometry (profile shape, maximum profile thickness), (ii) to investigate the influence of modelling parameters (turbolence modelling, flow solver spatial discretization schemes, temporal resolution) and (iii) to gain insight into the underlying physics (analysis of shock-buffet excitation mechanism).