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Condensation Modelling of Expanding Cold Gas Jets during Hypersonic Retro-Propulsion Manoeuvres within the RETPRO Project

Bykerk, Tamas and Kirchheck, Daniel and Karl, Sebastian and Fechter, Stefan (2022) Condensation Modelling of Expanding Cold Gas Jets during Hypersonic Retro-Propulsion Manoeuvres within the RETPRO Project. In: Proceedings of the Australasian Fluid Mechanics Conference (440), pp. 1-8. Australasian Fluid Mechanics Society. 23rd Australasian Fluid Mechanics Conference, 2022-12-04 - 2022-12-08, Sydney, Australia. ISSN 2653-0597.

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Official URL: https://www.afms.org.au/proceedings/23/Bykerk_et_al_2022.pdf

Abstract

The RETPRO project (Validation of Wind Tunnel Test and CFD Techniques for Retropropulsion), as part of ESA’s Future Launchers Preparatory Programme, aims at preparing the tools, necessary for a reliable design and simulation of future rocket launchers or spacecraft. A particular focus is assigned to vertical take-off and landing configurations using retro propulsion as part of their control concept for entry, descent, and landing manoeuvres. Wind tunnel tests and computational fluid dynamics are used to generate a comprehensive aerodynamic database, which is required for flight dynamics simulations, enabling mission and performance analyses of possible future launcher designs. Windtunnel tests are conducted in the DLR Cologne H2K facility, with room temperature dry air ejected through selected nozzles to simulate the exhaust plume. Condensation effects might occur in the plume due to the low static freestream pressure at Mach 7, combined with the expanding flow in the nozzle. This paper presents results from numerical investigations including a vapour-equilibirum model which evaluate the potential influence of plume condensation on measured data in the wind tunnel. A qualitative comparison between experimental and numerical results is presented through Schlieren photographs. Condensation was observed in the numerical results, causing the flow path in and around the plume to be altered. Surface pressure coefficients in the condensation case were observed to be approximately 5% lower than when using the standard ideal gas model. Finally, the shock stand off distance was reduced, but not significantly. The comparison with tunnel data was therefore more-or-less the same as with the ideal gas model and the use of the condensation model was not deemed necessary for subsequent computations.

Item URL in elib:https://elib.dlr.de/192038/
Document Type:Conference or Workshop Item (Speech)
Title:Condensation Modelling of Expanding Cold Gas Jets during Hypersonic Retro-Propulsion Manoeuvres within the RETPRO Project
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Bykerk, TamasUNSPECIFIEDhttps://orcid.org/0000-0001-8662-3484UNSPECIFIED
Kirchheck, DanielUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Karl, SebastianUNSPECIFIEDhttps://orcid.org/0000-0002-5558-6673UNSPECIFIED
Fechter, StefanUNSPECIFIEDhttps://orcid.org/0000-0001-5683-4715UNSPECIFIED
Date:5 December 2022
Journal or Publication Title:Proceedings of the Australasian Fluid Mechanics Conference
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Page Range:pp. 1-8
Publisher:Australasian Fluid Mechanics Society
ISSN:2653-0597
Status:Published
Keywords:Hypersonic, retro-propulsion, spacecraft, reusable
Event Title:23rd Australasian Fluid Mechanics Conference
Event Location:Sydney, Australia
Event Type:international Conference
Event Start Date:4 December 2022
Event End Date:8 December 2022
Organizer:Australasian Fluid Mechanics Society
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 , Köln-Porz
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Spacecraft, GO
Institute for Aerodynamics and Flow Technology > Supersonic and Hypersonic Technology
Deposited By: Bykerk, Tamas
Deposited On:12 Dec 2022 15:09
Last Modified:24 Apr 2024 20:53

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