Bodo Reimann
German Aerospace Center
Network
Latest external collaboration on country level. Dive into details by clicking on the dots.
Publication
Featured researches published by Bodo Reimann.
20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference | 2015
Sil van Brummen; Giuseppe Pezzella; Giovanni Andreutti; Bodo Reimann; Johan Steelant
This paper deals with the aerodynamic performance analysis of the expendable Experimental Flight Test Vehicle under development in the seventh framework programme, namely HEXAFLY-INT. A mission scenario, the different flight segments and events to which the payload is exposed to are described and justified. This allowed the definition of the aerothermo-mechanical loads required to conceptually design all elements on board of the vehicle. This flying test bed is a self-controlled glider configuration that shall face a hypersonic flight starting at about Mach 8, just after the separation from the experimental support module at about 50 km altitude, up to vehicle loss. During this flight, several experiments shall be carried out. The appraisal of the vehicle aerodynamic performance is needed for Flight Mechanics and Guidance, Navigation and Control analysis. In particular, hinge line moments for the EFTV’s aileron are also addressed to design the actuation line and to select the actuator device itself. The vehicle made maximum use of databases, expertise, technologies and materials elaborated in previously European community co-funded projects ATLLAS I & II, LAPCAT I & II, and HEXAFLY.
48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition | 2010
Bodo Reimann; Volker Hannemann
In the framework of validation and further development of the DLR TAU code for hypersonic applications several laminar calculations were conducted participating in a RTO working group. The enthalpy in the generic test cases ranges from 5 to 22 MJ/kg addressing thermo-chemical relaxation processes in air and pure nitrogen. Strong bow shocks as well as boundary layer separation, shock-shock and shock-boundary layer interactions are present in the flow fields. The applied numerical models are discussed. The comparison with the experimental data shows the current capability of the DLR TAU code to predict the aero-thermodynamic loads and how model improvements can be supported by these experiments.
Archive | 2004
Bodo Reimann; Ian Johnston; Volker Hannemann
The development of an equilibrium chemistry model for the DLR τ-Code has extended its ability to simulate high enthalpy flows, such as those around reentry vehicles or within high speed test facilities. Details of the development of the chemistry model, and some test cases, are included in this paper. Also presented is an improved axisymmetry treatment for the code, aimed at producing accurate and noise-free solutions for common hypersonic applications such as blunt bodies and shock tunnels.
Archive | 2009
Bodo Reimann; Volker Hannemann; Klaus Hannemann
The numerical simulation of discontinuous flow phenomena results in high demands related to the used computational grids. A high resolution of the grid is required to resolve shock waves and contact surfaces. This leads, especially for unsteady flows with moving structures, to grids with a large number of points. Local mesh adaptation allows to reduce the computational effort by refining the mesh only in regions where it is necessary. In the present paper a numerical simulation of the shock tunnel flow in the High Enthalpy Shock Tunnel G¨ottingen (HEG) is performed. Local grid adaptation is used to capture shocks and contact discontinuities. Of particular interest for the shock tunnel performance and the investigation of driver gas contamination is the shock reflection process and the interaction between the reflected shock, the boundary layer and the contact surface separating the test gas from the driver gas.
19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference | 2014
Yi Li; Bodo Reimann; Thino Eggers
The hot staging dynamics of a multistage rocket is studied using the coupled simulation of Computational Fluid Dynamics (CFD) and Flight Mechanics (FM). In the coupled simulations, the free-stream is modeled as “cold air” and the exhausted plume from the continuing-stage-motor is modeled with an equivalent calorically-perfect-gas that approximates the properties of the plume at the nozzle exit. The Navier-Stokes equations in the coupled simulations are time-accurately solved in moving system, with which the Flight Mechanics equations can be fully coupled. The Chimera mesh technique is utilized to deal with the relative motions of the separated stages. A few representative staging cases with different initial flight conditions of the rocket are studied with the coupled simulation. Based on the simulation results, the staging dynamics of the rocket are finally analyzed.
Progress in Aerospace Sciences | 2012
Doyle Knight; Jose Longo; Dimitris Drikakis; Datta V. Gaitonde; Andrea Lani; Ioannis Nompelis; Bodo Reimann; Louis Walpot
Progress in Aerospace Sciences | 2017
Doyle Knight; Olivier Chazot; Joanna Austin; Mohammad Ali Badr; Graham V. Candler; Bayram Celik; Donato de Rosa; Raffaele Donelli; Jeffrey R. Komives; Andrea Lani; Deborah A. Levin; Ioannis Nompelis; Marco Panesi; Giuseppe Pezzella; Bodo Reimann; Ozgur Tumuklu; Kemal Yuceil
18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference | 2012
Yi Li; Thino Eggers; Bodo Reimann
Acta Astronautica | 2014
Yi Li; Bodo Reimann; Thino Eggers
21st AIAA International Space Planes and Hypersonics Technologies Conference | 2017
Marco Marini; Giuseppe Pezzella; Antonio Schettino; Sara Di Benedetto; Victor Fernandez Villace; Johan Steelant; Anatoly Gubanov; Nina Voevodenko; Bodo Reimann; Craig Walton