Experiments on aerothermoelastic fluid–structure interaction in hypersonic flow

Aerothermoelastic fluid–structure interaction (FSI) is a crucial problem in the design of supersonic and hypersonic vehicles, but modeling capabilities are many cases quite limited. Insufficient treatment FSI can limit options or lead to damage loss vehicles. To improve understanding such problems, we conducted experiments with thin panels flow wind tunnel H2K at DLR, Cologne, where both thermal pressure-driven effects be observed. Both without turbulent shock-wave/boundary-layer (SWBLI) were considered. We obtained severe dynamic which led failure thinner panel. The results show strong dependency dynamics coupled system on small temperature changes. Furthermore, demonstrated that large incident shock angle facilitates flutter it would not occur shock. Detailed reference regarding aerothermal heating, wall pressure properties field using rigid structure. This extends very limited experimental data base serving as for preparation new experiments.