Wind tunnel installation effects on a high-speed exhaust flow under large blockage

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dc.contributor.authorTsentis, Spyros
dc.contributor.authorGoulos, Ioannis
dc.contributor.authorDebiasi, Marco
dc.contributor.authorPrince, Simon
dc.contributor.authorPachidis, Vassilios
dc.contributor.authorZmijanovic, Vladeta
dc.contributor.authorSaavedra, Josè
dc.date.accessioned2025-05-21T13:00:30Z
dc.date.available2025-05-21T13:00:30Z
dc.date.freetoread2025-05-21
dc.date.issued2025-05-19
dc.date.pubOnline2025-05-19
dc.description.abstractThis study presents a numerical investigation of wind tunnel installation effects on the exhaust flow for a high-speed system under a blockage ratio of 16.5%. The configuration features a nozzle and a cavity embedded at the base of an ogive-cylindrical body and is representative of future, high-speed exhausts. The work is motivated by the need of testing large, powered-on models and the size of most closed transonic tunnels available in academic research facilities. This combination leads to high blockage ratios and therefore severe flow distortion. The objective is to examine the installation effects and quantify the base flow similarity relative to unbounded conditions. The numerical approach is validated against experimental data. A jet vectoring effect is identified due to the pylon, which is intensified under choked tunnel operation. Additionally, a methodology is proposed, which allows base pressure to be compared to unbounded flow conditions. Results show that the pressure distribution agrees within 1.5% and 0.1% for the base and cavity walls, respectively. This demonstrates that local aerodynamic similarity can be established between large-blockage, tunnel-tested conditions and unbounded flow through the proposed approach. This enables the use of small-scale facilities for base flow studies of high-speed exhausts under large blockage.
dc.description.journalNameJournal of Spacecraft and Rockets
dc.description.sponsorshipThe authors would like to express their gratitude to Reaction Engines Ltd., Rolls-Royce Plc, and the Cranfield Air and Space Propulsion Institute (CASPI) for funding this project and granting permission to publish this research.
dc.format.extentpp. xx-xx
dc.identifier.citationTsentis S, Goulos I, Debiasi M, et al., (2025) Wind tunnel installation effects on a high-speed exhaust flow under large blockage. Journal of Spacecraft and Rockets, Available online 19 May 2025
dc.identifier.eissn1533-6794
dc.identifier.elementsID673295
dc.identifier.issn0022-4650
dc.identifier.issueNoahead-of-print
dc.identifier.urihttps://doi.org/10.2514/1.a36092
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/23905
dc.identifier.volumeNoahead-of-print
dc.languageEnglish
dc.language.isoen
dc.publisherAmerican Institute of Aeronautics and Astronautics (AIAA)
dc.publisher.urihttps://arc.aiaa.org/doi/10.2514/1.A36092
dc.rightsAttribution-NonCommercial 4.0 Internationalen
dc.rights.urihttp://creativecommons.org/licenses/by-nc/4.0/
dc.subjectAerospace & Aeronautics
dc.subject4001 Aerospace engineering
dc.titleWind tunnel installation effects on a high-speed exhaust flow under large blockage
dc.typeArticle
dcterms.dateAccepted2025-02-23

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