Base flow characteristics for a sub-scale high-speed exhaust at over-expanded mode

Simple item page
dc.contributor.authorTsentis, Spyros
dc.contributor.authorGoulos, Ioannis
dc.contributor.authorPrince, Simon
dc.contributor.authorPachidis, Vassilios
dc.contributor.authorZmijanovic, Vladeta
dc.date.accessioned2024-10-23T13:21:24Z
dc.date.available2024-10-23T13:21:24Z
dc.date.freetoread2024-10-23
dc.date.issued2024-10-07
dc.date.pubOnline2024-10-07
dc.description.abstractThis paper presents a numerical investigation on the base flow characteristics of a sub-scale, high-speed exhaust system at over-expanded state. The geometry is representative of future, advanced propulsion concepts. It features a truncated, ideal-contoured (TIC) nozzle and an axisymmetric cavity embedded at the base. Scale resolving simulations are performed using the Delayed Detached Eddy Simulation (DDES) turbulence modelling approach. The configuration is mounted on the test section of a wind tunnel through a wing-pylon to facilitate ongoing experiments. The proper orthogonal decomposition (POD) method is employed to identify the salient flow features at the base in terms of energy content. Time-averaged base pressure results show slightly reduced levels of pressure behind the pylon by approximately 1.2%. Additionally, reduced levels of pressure fluctuations in the region directly downstream of the pylon are identified, suggesting a severe impact on the base flow. This is further confirmed through the modal decomposition of the base flow. The first two most energetic modes of the flow exhibit strong spatial asymmetry in the intensity of velocity fluctuations, the latter being significantly reduced in the region behind the pylon. This is important for future, high-speed vehicles, which typically employ wingtip mounted nacelles and could exhibit increased levels of side loads as a result of this azimuthal asymmetry in the flow development.
dc.description.conferencename34th Congress of the International Council of the Aeronautical Sciences
dc.description.sponsorshipThe authors would like to express their gratitude to Reaction Engines Ltd. and the Cranfield Air and Space Propulsion Institute (CASPI) for funding this project and for granting permission to publish this research.
dc.identifier.citationTsentis S, Goulos I, Prince S, et al., (2024) Base flow characteristics for a sub-scale high-speed exhaust at over-expanded mode. In: 34th Congress of the International Council of the Aeronautical Sciences, 9-13 September 2024, Florence, Italy
dc.identifier.elementsID554598
dc.identifier.issn2958-4647
dc.identifier.urihttps://www.icas.org/ICAS_ARCHIVE/ICAS2024/data/papers/ICAS2024_0512_paper.pdf
dc.identifier.urihttps://www.icas.org/ICAS_ARCHIVE/ICAS2024/data/preview/ICAS2024_0512.htm
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/23107
dc.language.isoen
dc.publisherICAS - International Council of the Aeronautics Sciences
dc.publisher.urihttps://www.icas.org/ICAS_ARCHIVE/ICAS2024/icas2024_materials.html
dc.rightsAttribution 4.0 Internationalen
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/
dc.subjectbase flow
dc.subjecthigh-speed exhausts
dc.subjectbase drag
dc.subjectDDES
dc.subjectPOD
dc.titleBase flow characteristics for a sub-scale high-speed exhaust at over-expanded mode
dc.typeConference paper
dcterms.coverageFlorence, Italy
dcterms.dateAccepted2024-03-28
dcterms.temporal.endDate13 Sep 2024
dcterms.temporal.startDate9 Sep 2024

Files

Original bundle
Now showing 1 - 1 of 1
Thumbnail Image
Name:
Base_flow_characteristics_for_a_sub-scale-2024.pdf
Size:
2.61 MB
Format:
Adobe Portable Document Format
Download
License bundle
Now showing 1 - 1 of 1
No Thumbnail Available
Name:
license.txt
Size:
1.63 KB
Format:
Plain Text
Description:
Download

Collections

Staff publications (SATM)