Experimental data from ramjet/scramjet combustion and numerical validation perspectives

This work is the result of a cooperation agreement between SPLab of Politecnico di Milano and ICMATE-CNR (National Research Council). In particular two different configurations of a rectangular geometry small scale model engine fuelled with gaseous hydrogen were tested at Mach 5.4 in a high enthalpy pulse facility. The focus was put first on a dual-mode scramjet setup in order to obtain the main propulsion parameters for a wide ER range. Another geometry, corresponding to a ramjet configuration, was subsequently evaluated under the same nominal freestream flow and fuelling conditions. It was observed that under the tested flight conditions, the ramjet setup featured higher specific impulses.