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Advance of Scramjet Operating Mode Comprehension based on Shock Tunnel Experiments and Numerical Modelling

Hannemann, Klaus (2018) Advance of Scramjet Operating Mode Comprehension based on Shock Tunnel Experiments and Numerical Modelling. In: 69th International Astronautical Congress (IAC). 69th International Astronautical Congress (IAC), 1.-5. Oktober 2018, Bremen, Deutschland.

Full text not available from this repository.

Official URL: https://www.iac2018.org/program/scientific-program/

Abstract

For future hypersonic transport aircraft or space launch vehicles based on combined cycle engines, the supersonic combustion ramjet (scramjet) is a promising component of the propulsion system. In particular for atmospheric flight Mach numbers in excess of 8, shock tunnel facilities are well suited to duplicate these flight conditions. The focus of the present article is to provide a review of selected important achievements obtained in free piston driven shock tunnel facilities. Research activities conducted in laboratories around the globe will be highlighted followed by a more detailed discussion of the combined experimental and numerical work performed on hydrogen fuelled integrated scramjet configurations at the German Aerospace Center (DLR). The ground based testing was conducted in the High Enthalpy Shock Tunnel Göttingen (HEG) and the computations were performed utilizing the DLR TAU code. Among the considered configurations is the Australian HyShot II flight test vehicle. It is considered to be well suited for fundamental combustor investigations and numerical tool validation purposes. Benchmark data were compiled in HEG related to different combustor modes. These data are related to the nominal operating mode and additionally to the response of the HyShot II combustor to equivalence ratios close to the critical value at which the onset of thermal choking occurs. The detailed analysis of the developing shock train and its unexpected behaviour revealed new insight into the combustor flow generated by localized thermal choking. A small scale flight experiment was designed in the framework of the European Commission co-funded LAPCAT II project. The complete scramjet flow path was subsequently tested in HEG and the numerically predicted positive aero-propulsive balance could be demonstrated by utilizing the free flight force measurement technique based on optical tracking.

Item URL in elib:https://elib.dlr.de/123265/
Document Type:Conference or Workshop Item (Speech)
Title:Advance of Scramjet Operating Mode Comprehension based on Shock Tunnel Experiments and Numerical Modelling
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Hannemann, Klausklaus.hannemann (at) dlr.deUNSPECIFIED
Date:October 2018
Journal or Publication Title:69th International Astronautical Congress (IAC)
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:supersonic combustion ramjet, free piston driven shock tunnel, hydrogen combustion, ground based testing, numerical modelling
Event Title:69th International Astronautical Congress (IAC)
Event Location:Bremen, Deutschland
Event Type:international Conference
Event Dates:1.-5. Oktober 2018
Organizer:International Astronautical Federation
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 - Wiederverwendbare Raumfahrtsysteme und Antriebstechnologie
Location: Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Spacecraft, GO
Deposited By: Hannemann, Prof. Dr. Klaus
Deposited On:20 Nov 2018 18:51
Last Modified:20 Nov 2018 18:51

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