Strauss, Friedolin and General, Stephan and Cragg, Patrick and Schlechtriem, Stefan (2020) Wall Pressure Effects and Shock-Boundary Layer Interactions in a Transpiration Cooled Scramjet Model Combustor. In: 23rd AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2020. 23rd AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 10.-12. März 2020, Montreal, Quebec, Kanada. doi: 10.2514/6.2020-2438. ISBN 978-162410600-2.
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Official URL: https://arc.aiaa.org/doi/10.2514/6.2020-2438
Abstract
This publication presents results of the ongoing investigation of transpiration cooling of scramjets conducted at the German Aerospace Center (DLR). It summarizes the results on the influence of the shock-boundary layer interaction on the static wall pressure distribution downstream of the transpiration cooling system obtained in more than 1000 hot run tests. Special focus is placed on the local static pressure distribution in the coolant wake region on the combustion chamber’s upper wall. Furthermore, different flow interaction phenomena were discovered and are thoroughly analyzed by the application of state of the art optical and intrusive measurement techniques like Background Oriented Schlieren (BOS) combined with pressure data analysis and correlation. The unique SBLI behavior of two coolants (hydrogen and nitrogen) and their influence on the static wall pressure distribution gets addressed in this publication. Three different porous wall materials are compared and analyzed in terms of performance, sensitivity to shock- boundary layer interaction issues and their influence on the wall pressure in the coolant wake region. An outlook is presented on the results of additional experiments using different types of porous media (e.g. ceramics) and improved measurement techniques with the same coolants. Further research requirements and subsequent changes in the test setup are discussed.
Item URL in elib: | https://elib.dlr.de/139955/ | |||||||||||||||
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Document Type: | Conference or Workshop Item (Speech) | |||||||||||||||
Title: | Wall Pressure Effects and Shock-Boundary Layer Interactions in a Transpiration Cooled Scramjet Model Combustor | |||||||||||||||
Authors: |
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Date: | 1 April 2020 | |||||||||||||||
Journal or Publication Title: | 23rd AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2020 | |||||||||||||||
Refereed publication: | Yes | |||||||||||||||
Open Access: | No | |||||||||||||||
Gold Open Access: | No | |||||||||||||||
In SCOPUS: | Yes | |||||||||||||||
In ISI Web of Science: | No | |||||||||||||||
DOI : | 10.2514/6.2020-2438 | |||||||||||||||
ISBN: | 978-162410600-2 | |||||||||||||||
Status: | Published | |||||||||||||||
Keywords: | Transpiration Cooling, Fluid Dynamics, Thermodynamics, Scramjet, Hypersonics, High-Speed Air Breathing Propulsion, Ground Testing | |||||||||||||||
Event Title: | 23rd AIAA International Space Planes and Hypersonic Systems and Technologies Conference | |||||||||||||||
Event Location: | Montreal, Quebec, Kanada | |||||||||||||||
Event Type: | international Conference | |||||||||||||||
Event Dates: | 10.-12. März 2020 | |||||||||||||||
Organizer: | AIAA - American Institute of Aeronautics and Astronautics, CASI / IASC | |||||||||||||||
HGF - Research field: | Aeronautics, Space and Transport | |||||||||||||||
HGF - Program: | Space | |||||||||||||||
HGF - Program Themes: | other | |||||||||||||||
DLR - Research area: | Raumfahrt | |||||||||||||||
DLR - Program: | R - no assignment | |||||||||||||||
DLR - Research theme (Project): | R - no assignment | |||||||||||||||
Location: | Lampoldshausen | |||||||||||||||
Institutes and Institutions: | Institute of Space Propulsion > Propellants Institute of Space Propulsion > Leitungsbereich RA Institute of Space Propulsion > Engineering | |||||||||||||||
Deposited By: | Strauss, Friedolin | |||||||||||||||
Deposited On: | 04 Jan 2021 08:27 | |||||||||||||||
Last Modified: | 14 Mar 2022 14:40 |
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