Reynolds Number Scaling Effects in Transonic Cavity Aerodynamics: A High-Fidelity Experimental and Numerical Framework

Kurzfassung

This paper outlines a comprehensive research framework designed to isolate and quantify the non-linear effects of Reynolds number on transonic cavity flows. Current semi-empirical prediction models often rely on low Reynolds number wind tunnel data, which may not accurately represent the shear layer dynamics and acoustic loading encountered at flight conditions. This study proposes a combined approach utilizing the Cryogenic Ludwieg-Tube in Göttingen (KRG) to independently vary Reynolds number while maintaining constant Mach number, alongside with high-fidelity numerical simulations. The methodology aims to determine how boundary layer scaling influences the amplitude and frequency of Rossiter modes, bridging the gap between sub-scale testing and full-scale operational environments.