For the development of advanced materials and structures with improved corrosion and abrasion resistance, a better understanding of the complex multiphase flow/structure interaction is necessary. Besides appropri-ate material development of ceramic matrix composites (CMC) materials concerning the harsh applica-tion conditions, a precise material characterization with respect to compatibility to relevant fuels on aging aspects and, especially, to performance on application-related combustion tests for ramjet and scramjet propulsion are of special interest. In order to test and evaluate different silicon carbide (SiC) contents on the surface of different C/C-SiC materials, two different materials of quality XS (standard) and an enhanced C/C-SiC material with SiC enriched surface and graded structural lay-up were developed, manufactured, characterized, and tested at DLR's test facility M11 at scramjet conditions. This facility is able to produce the boundary conditions typical of a scramjet/ramjet propelled flight at Mach 5.5 to Mach 6.0 flight at an al-titude of 30 km in the connected pipe ground test configuration. It is capable of stagnation temperatures up to 1500 K, 25 bar stagnation pressure, and 5 kg/s hot gas mass flow rate. The material samples were exposed to the vitiated air in a scramjet model combustion chamber with lateral optical access and a wedge-shaped shock generator similar to flame holder geometries This publication gives both a detailed overview of the ma-terial and component development and an overview of the hot gas testing facility and its capabilities for test-ing materials and components. In addition, some typical results of tested C/C-SiC materials are presented.
