01.2 - Aircraft Design and Integrated System (Applications)
CONCEPTUAL AIRCRAFT DESIGN OF A RESEARCH BASELINE WITH DIRECT LIQUID HYDROGEN COMBUSTION
M. Kotzem¹, S. Wöhler¹, T. Burschyk¹, C. Hesse¹, S. Hellbrück¹, T. Zill¹; ¹German Aerospace Center (DLR), Germany
This study addresses the conceptual aircraft design of a short-medium range research baseline with direct liquid hydrogen combustion and an assumed technology in 2035. The final aircraft design is based on the results of aircraft design and sensitivity studies focusing on the integration of the LH2 tanks and systems, and can be used as a reference point for future research efforts.