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Transpiration cooling experiments in free-piston shock tunnel HIEST

Tanno, H. and Komuro, T. and Itoh, K. and Kuhn, Markus and Petkov, Ivaylo and Esser, Burkard (2016) Transpiration cooling experiments in free-piston shock tunnel HIEST. 8th European Workshop on Thermal Protection Systems and Hot Structures, 19.-22. April 2016, Noordwijk, Niederlande.

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Official URL: http://congrexprojects.com/custom/16c07/


Transpiration cooling technique is one of the most promising candidates as the next‐generation TPS ‐thermal protection system for reentry or planetary entry vehicles. Although many researchers have produced numerous works over these decades to use the technique to cool spacecraft or aircraft components, which are exposed to high heat‐load, such as rocket engines or gas‐turbine blades. Nevertheless, most of the studies were focusing on the applications in a turbulent boundary layer. On the other hand, planetary entry or reentry vehicles have to fly from hypersonic to subsonic speed. Since flight altitude is also changed from the space to the ground, Reynolds number will change from fully‐laminar to fully‐turbulent condition. Moreover, the extremely high flightspeed will produce thermochemical non‐equilibrium flow in the boundary layer. For the application of the cooling technique on reentry vehicle design, it is crucial to address the knowledge about the characteristic of transpiration effects on boundary layer under such the extreme high‐stagnation flow condition. Recent studies were all carried in low‐density flow, or in perfect gas flow (low enthalpy flow), under which flow condition does not agree to real flight condition. The free‐piston shock tunnel HIEST, which can produce high‐enthalpy and high‐density namely high‐Reynolds number test free‐steam suitable for the study of transpiration cooling. The aim of the present research is to obtain transpiration cooling characteristics with a generic flat plate in HIEST under high stagnation enthalpy and pressure condition, which stagnation enthalpy was 4 to 20MJ/kg and stagnation pressure was 12MPa to 60MPa. The transpiration cooling on the flat plate surface was conducted with Helium or Nitrogen gas injection through a porous material located downstream of the leading edge, which material had already used for previous Hypersonic studies. Heat flux distribution on the flat plate was measured along the centerline. The small amount of gas‐injection reduces surface heat flux. Even so, heat flux augmentation was observed with large amount of gas‐injection due to the onset of early transition of the boundary layer.

Item URL in elib:https://elib.dlr.de/105525/
Document Type:Conference or Workshop Item (Speech)
Title:Transpiration cooling experiments in free-piston shock tunnel HIEST
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Kuhn, MarkusMarkus.Kuhn (at) dlr.deUNSPECIFIED
Petkov, IvayloIvaylo.Petkov (at) dlr.deUNSPECIFIED
Esser, BurkardBurkard.Esser (at) dlr.deUNSPECIFIED
Date:July 2016
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:Transpiration cooling, Atmospheric entry, High enthalpy testing, Non-Equilibrium flow, Porous media, Shock tunnel
Event Title:8th European Workshop on Thermal Protection Systems and Hot Structures
Event Location:Noordwijk, Niederlande
Event Type:international Conference
Event Dates:19.-22. April 2016
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - Raumfahrzeugsysteme - Rückkehrtechnologie
Location: Köln-Porz , Stuttgart
Institutes and Institutions:Institute of Structures and Design > Space System Integration
Institute of Aerodynamics and Flow Technology > Über- und Hyperschalltechnologien
Deposited By: Esser, Dr.-Ing. Burkard
Deposited On:05 Sep 2016 09:10
Last Modified:01 Dec 2018 19:52

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