Numerical characterization of hot nozzle wall impact on launch vehicle base flows (B05)

• Subject Area: Fluid Mechanics
• Term: from 2008 to 2020
• Project identifier: Deutsche Forschungsgemeinschaft (DFG) - Project number 26293245

Within the roadmap to a numerical model of a realistic base flow scenario the hot plume resulting from a nearly stoichiometric combustion is taken into account. A plume generated inside the launch vehicle model will heat up the structure. A fluid-structure coupling strategy will be applied to determine the surface temper-atures. Subsequently, the sensitivity of the dynamics of the unsteady rocket base flow including the hot plume in transonic ambient flow will be quantified with respect to these surface temperatures applying hy-brid RANS/LES methods. The emerging mechanical and thermal loads on the nozzle structures are key re-sults required for future technology demonstration activities.

• DFG Programme: CRC/Transregios
• Subproject of: TRR 40: Technological Foundations for the Design of Thermally and Mechanically Highly Loaded Components of Future Space Transportation Systems
• Applicant Institution: Technische Universität München (TUM)
• Co-Applicant Institution: Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR)
• Project Heads: Dr.-Ing. Thino Eggers; Dr. Volker Hannemann; Professor Dr.-Ing. Klaus Hannemann