Analysis of a Two-Staged Supersonic Combustion Chamber using Experiments and Simulations

Abstract

Scramjet engines are expected to decrease the cost for access to space immensely. But due to manifold physical challenges, theses engines are far away from series production. Experimental studies are dicult to perform and ight tests are rather expensive. Numerical studies are, therefore, often used to perform parameter studies within the relevant Mach number regime. Nevertheless, systematic experimental data are essential when validating numerical studies. The present study focuses on a two-staged supersonic combustion chamber and hereby joins numerical studies with experimental validation and investigation. Previous studies with a two-staged combustor have proven to have advantages compared to the single-staged design. Investigations with the single-staged central injector concept