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Title:Eksperimentalno in numerično raziskovanje nestacionarnega tokovnega polja okoli osamljenega krila
Authors:ID Fike, Matej (Author)
ID Bombek, Gorazd (Author)
ID Hribernik, Aleš (Author)
Files:URL http://www.drustvozamehaniko.si/zbornik/ZbornikKD2011.pdf
 
Language:Slovenian
Work type:Unknown
Typology:1.08 - Published Scientific Conference Contribution
Organization:FS - Faculty of Mechanical Engineering
Abstract:V članku je predstavljena raziskava vpliva turbulentnega modela na izračunano tokovno polje osamljenega krila v majhnem vetrovniku. Medsebojno so bili primerjani numerični in eksperimentalni rezultati preko točke odcepitve, tlačnega poteka po krilu in tokovnega polja vključno z oscilacijami hitrosti pri obtekanju. Eksperimentalni podatki so bili zajeti s pomočjo tlačnih senzorjev in PIV (Particle Image Velocimetry) merilnega sistema. Raziskava je bila opravljena za različne napadne kote.
Keywords:ventilatorji, vetrovnik, PIV merilni sistem, tokovna hitrostna polja
Year of publishing:2011
PID:20.500.12556/DKUM-26868 New window
UDC:533.6.013
COBISS.SI-ID:15398422 New window
NUK URN:URN:SI:UM:DK:4ZYQGUX6
Publication date in DKUM:01.06.2012
Views:2081
Downloads:63
Metadata:XML DC-XML DC-RDF
Categories:Misc.
:
FIKE, Matej, BOMBEK, Gorazd and HRIBERNIK, Aleš, 2011, Eksperimentalno in numerično raziskovanje nestacionarnega tokovnega polja okoli osamljenega krila. In : [online]. Published Scientific Conference Contribution. 2011. [Accessed 15 March 2025]. Retrieved from: http://www.drustvozamehaniko.si/zbornik/ZbornikKD2011.pdf
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Secondary language

Language:English
Title:Experimental and numerical investigation of unsteady field around an isolated airfoil
Abstract:A study was performed to analyse the influence of a turbulent model on the flow-field and integral characteristics of an isolated airfoil within a small wind-tunnel, and to find the most suitable turbulent model. The selection was made by a comparison of the numerical and experimental results for flow separation point position, the airfoil pressure-distribution on the airfoil, and the velocity profile including velocity oscillations. The experimental results were acquired using pressure sensors and PIV (Particle Image Velocimetry). The study was performed at various angles of attack (AOA).


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