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Wall Pressure Effects and Shock-Boundary Layer Interactions in a Transpiration Cooled Scramjet Model Combustor

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: Hypersonics 2020 Conference Proceedings. 23rd AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 10.-12. März 2020, Montreal, Quebec, Kanada. doi: 10.2514/6.2020-2438.

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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/
Document Type:Conference or Workshop Item (Speech)
Title:Wall Pressure Effects and Shock-Boundary Layer Interactions in a Transpiration Cooled Scramjet Model Combustor
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Strauss, FriedolinFriedolin.Strauss (at) dlr.dehttps://orcid.org/0000-0002-1385-4326
General, StephanStephan.General (at) dlr.dehttps://orcid.org/0000-0001-5606-882X
Cragg, PatrickPatrick.Cragg (at) dlr.deUNSPECIFIED
Schlechtriem, StefanStefan.Schlechtriem (at) dlr.dehttps://orcid.org/0000-0002-3714-9664
Date:1 April 2020
Journal or Publication Title:Hypersonics 2020 Conference Proceedings
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
DOI :10.2514/6.2020-2438
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:04 Jan 2021 08:27

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