Full metadata record
| DC pole | Hodnota | Jazyk |
|---|---|---|
| dc.contributor.author | Klesa, J. | |
| dc.contributor.author | Hejna, J. | |
| dc.contributor.author | LeNours, V. | |
| dc.contributor.author | Čenský, T. | |
| dc.contributor.editor | Adámek, Vítězslav | |
| dc.contributor.editor | Jonášová, Alena | |
| dc.contributor.editor | Plánička, Stanislav | |
| dc.contributor.editor | Zajíček, Martin | |
| dc.date.accessioned | 2019-01-16T08:36:39Z | - |
| dc.date.available | 2019-01-16T08:36:39Z | - |
| dc.date.issued | 2018 | |
| dc.identifier.citation | Computational mechanics 2018: book of extended abstracts: 34th conference with international participation, p. 37-38. | en |
| dc.identifier.isbn | 978-80-261-0819-1 | |
| dc.identifier.uri | http://hdl.handle.net/11025/30796 | |
| dc.identifier.uri | https://www.zcu.cz/export/sites/zcu/pracoviste/vyd/online/FAV_Computational_Mechanics_2018.pdf | |
| dc.format | 2 s. | cs |
| dc.format.mimetype | application/pdf | |
| dc.language.iso | en | en |
| dc.publisher | Západočeská univerzita v Plzni | cs |
| dc.relation.ispartofseries | Computational Mechanics | en |
| dc.rights | Copyright © 2018 University of West Bohemia, Plzeň, Czech Republic | en |
| dc.subject | UL-39 ultralehké letadlo | cs |
| dc.subject | chladic� syst�m | cs |
| dc.subject | modelový ventilátor | cs |
| dc.title | Influence of the cooling bypass on the aircraft nozzle outflow | en |
| dc.type | konferenční příspěvek | cs |
| dc.type | conferenceObject | en |
| dc.rights.access | openAccess | en |
| dc.type.version | publishedVersion | en |
| dc.description.abstract-translated | UL-39 ultralight aircraft has been developed at the Department of Aerospace Engineering, Czech Technical University in Prague [3]. This aircraft is powered by unique propulsion system, which consists of a fan driven by piston engine. Various concepts of the cooling system with various radiator positions were studied. Radiator in the bypass channel behind fan is used at the flying prototype of UL-39. Test bed with the model fan was build in order to conduct test and experiments for the development of this propulsion system. Model of the UL-39 outlet duct is placed behind the fan, see Fig. 1. Radiator pressure loss is simulated by various inserts including clear frame (i.e., without pressure loss), honeycomb and screen. Bypass channel is is on the upper side of the outlet duct, i.e., on the opposite side than at the real UL-39 aircraft. Flow field behind the nozzle in the plane of symmetry is measured for each case by PIV (Particle Image Velocimetry) method for each case. Measurements were done in the wind tunnel at the Department of Aerospace Engineering. Fan RPM between 20,000 and 35,000 were used. | en |
| dc.subject.translated | UL-39 ultralight aircraft | en |
| dc.subject.translated | cooling system | en |
| dc.subject.translated | model fan | en |
| dc.type.status | Peer-reviewed | en |
| Vyskytuje se v kolekcích: | Computational mechanics 2018 Computational mechanics 2018 | |
Soubory připojené k záznamu:
| Soubor | Popis | Velikost | Formát | |
|---|---|---|---|---|
| Klesa.pdf | Plný text | 3,56 MB | Adobe PDF | Zobrazit/otevřít |
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