A5082664308- Gas Dynamics and Kinetic Theory
- Computational Fluid Dynamics and Aerodynamics
- Rocket and propulsion systems research
- Plasma and Flow Control in Aerodynamics
- Fluid Dynamics and Turbulent Flows
- Combustion and flame dynamics
- Combustion and Detonation Processes
- Particle Dynamics in Fluid Flows
- Plasma Diagnostics and Applications
- Spacecraft and Cryogenic Technologies
- Wind and Air Flow Studies
- Photochemistry and Electron Transfer Studies
- Aerodynamics and Fluid Dynamics Research
- Chemical Reactions and Mechanisms
- Aerodynamics and Acoustics in Jet Flows
- Radical Photochemical Reactions
- Electrohydrodynamics and Fluid Dynamics
- Heat transfer and supercritical fluids
- Laser-Plasma Interactions and Diagnostics
- Oxidative Organic Chemistry Reactions
- Astro and Planetary Science
- Magnetic confinement fusion research
- Fluid Dynamics and Vibration Analysis
- Phase Equilibria and Thermodynamics
- Radiative Heat Transfer Studies
Deutsches Zentrum für Luft- und Raumfahrt e. V. (DLR)
2013-2023
Justus-Liebig-Universität Gießen
2020-2022
China Aerodynamics Research and Development Center
2008-2011
The University of Queensland
2005
University of Southern Queensland
2005
Dienstleistungszentrum Ländlicher Raum
2002
Langley Research Center
1996
Novartis (Switzerland)
1988-1992
University of Cincinnati
1987-1990
University of Würzburg
1984-1989
The transition from old space to new along with increasing commercialization has a major impact on flight, in general, and electric propulsion (EP) by ion thrusters, particular. Ion thrusters are nowadays used as primary systems space. This article describes how these changes related affect various aspects that important for the development of EP systems. Starting historical overview flight technology systems, number missions underlying technologies presented. focus our discussion is radio...
Abstract An experimental and numerical investigation of the unsteady phenomena induced in a hydrogen-fuelled scramjet combustor under high-equivalence-ratio conditions is carried out, focusing on processes leading up to unstart. The configuration for study fuelled flow path HyShot II flight experiment. Experiments are performed HEG reflected-shock wind tunnel, results compared with those obtained from simulations. High-speed schlieren OH ∗ chemiluminescence visualization, together...
The design of hypersonic airbreathing vehicles is a challenging objective due to the intrinsic complexity propulsion-airframe integration in combination with an engine cycle able operate over wide Mach number range. This one objectives EC co-funded project LAPCAT-II aiming reduce antipodal flights less than 2 4 hours. Among several studied preceding LAPCAT-I, only aircraft designs for 5 and 8 were retained present project. Starting from available vehicle its related pre-cooled turbo-ramjet,...
Visualization experiments are performed to investigate the development of instability waves within boundary layer on a slender cone under high Mach number conditions. The experimental facility is reflected-shock wind tunnel, allowing both low (Mach-8 flight equivalent) and high-enthalpy conditions be simulated. Second-mode visualized using high-speed schlieren set-up, with pulse bursting light source propagation speed wavepackets unambiguously resolved. This, in combination wavelength...
The development of the wake behind a flat plate at supercritical Reynolds number ( Re = 200, based on thickness and free-stream velocity) is simulated numerically by solving two-dimensional unsteady Navier-Stokes equations with finite-difference Galerkin method. intermediate quasi-steady state investigated an Orr-Sommerfeld analysis for complex frequencies wavenumbers. Based this linear, local stability it can be shown that divided into regions absolute convective instability. One goal work...
AMINAR-turbulent transition in hypersonic boundary layers remains a challenging subject.This is especially true of the hypervelocity regime, which an intriguing phenomenon possible damping second-mode disturbances by chemical and vibrational nonequilibrium processes 1,2 .To generate flows with sufficiently high enthalpy to investigate such effects, use shock-tunnel facilities necessary; furthermore, it now generally accepted that direct measurements instability mechanisms active within...
Certain experiments in quasi-isobaric supercritical injection remain unexplained by the current state of theory: Without developing a constant value potential core as expected from mechanical view break-up, density is observed to drop immediately upon entering chamber. Furthermore, this phenomenon has never been captured computational fluid dynamics (CFD) despite having become de facto standard case for real CFD validation. In paper, we present strong evidence thermal jet disintegration...
A concise overview of the overall layout an experimental powered high-speed flight vehicle including its subsystems is given. mission scenario, different segments and events to which payload is exposed are described justified. This allowed definition aero-thermo-mechanical loads required conceptually design all elements on board vehicle. The final configuration could achieve objectives. In particular aero-propulsive balance, i.e. thrust ≥ drag lift weight, be established at a cruise Mach...
Testing of the HyShot II scramjet configuration was carried out in High Enthalpy Shock Tunnel Goettingen, HEG, German Aerospace Center, DLR. Computational fluid dynamics (CFD) is applied to support analysis experimental results and for prediction free stream conditions HEG test section. Numerical simulations flow complete fuel on off were performed. This paper describes laminar turbulent modeling approaches CFD presents numerical their comparison experiment both nozzle reacting Scramjet. The...
The High Enthalpy Shock Tunnel Göttingen (HEG) of the German Aerospace Center (DLR) is one major European hypersonic test facilities. It was commissioned for use in 1991 and utilized since then extensively a large number national international space flight projects. Originally, facility designed investigation influence high temperature effects such as chemical thermal relaxation on aerothermodynamics entry or re-entry vehicles. Over last years its range operating conditions subsequently...
A series of experiments has been carried out in the HEG facility (High Enthalpy Shock Tunnel, Gottingen) to obtain detailed measurements on HyShotII scramjet configuration under both steady and unsteady combustion conditions. Standard pressure are performed, but a main focus this campaign is use optical visualization techniques: high-speed visualizations OH* chemiluminescence together with pulsed-diode laser Schlieren imaging employed gain information about approximate flame location as well...
Combined free-stream disturbance measurements and receptivity studies in hypersonic wind tunnels were conducted by means of a slender wedge probe direct numerical simulation. The study comprises comparative tunnel noise at Mach 3, 6 7.4 two Ludwieg tube facilities shock tunnel. Surface pressure fluctuations measured over wide range frequencies test conditions including harsh environments not accessible to measurement techniques such as pitot probes hot-wire anemometry. Quantitative results...