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Hypersonic Airbreathing Propulsion Testing in Shock Tunnels Including Numerical Analysis

Hannemann, Klaus (2019) Hypersonic Airbreathing Propulsion Testing in Shock Tunnels Including Numerical Analysis. Summer School on Numerical Simulation and Measurement of Hypersonic Gas Dynamics and Combustion, 2019-07-22 - 2019-07-26, Xiamen, China.

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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/130018/
Document Type:Conference or Workshop Item (Speech)
Title:Hypersonic Airbreathing Propulsion Testing in Shock Tunnels Including Numerical Analysis
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Date:22 July 2019
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:supersonic combustion ramjet, free piston driven shock tunnel, hydrogen combustion, ground based testing, numerical modelling
Event Title:Summer School on Numerical Simulation and Measurement of Hypersonic Gas Dynamics and Combustion
Event Location:Xiamen, China
Event Type:international Conference
Event Start Date:22 July 2019
Event End Date:26 July 2019
Organizer:Xiamen University, School of Aerospace Engineering
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transportation
DLR - Research area:Raumfahrt
DLR - Program:R RP - Space Transportation
DLR - Research theme (Project):R - Reusable Space Systems and Propulsion Technology
Location: Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Spacecraft, GO
Deposited By: Hannemann, Prof. Dr. Klaus
Deposited On:08 Nov 2019 17:13
Last Modified:24 Apr 2024 20:33

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