Design of the Transpiration Cooled Fin Experiment FinEx II on HIFLIER1

Abstract

For hypersonic flight vehicles, sharp leading edges are integral part of the structure, such as air intakes, wing leading edges and stabilizer fins. However, due to the short standoff distance of the forming shock waves during hypersonic flight, these structures typically face severe thermal loads. In the present paper, transpiration cooling in combination with the application of ceramic matrix composites structures is investigated as a possible approach for novel hypersonic flight thermal protection for sharp leading edges. For this purpose, in the framework of the HIFLiER 1 flight research experiment, the DLR Institute of Structures and Design, in collaboration with the Institute of Space Systems of the University of Stuttgart, is responsible for the design and construction of an experimental module of the sounding rocket. The module will house four fins, whose leading edge is made of an inhouse-developed porous C/C-SiC material, which would allow the transpiration cooling application.