Optical and Hot-Film Measurements of the Boundary Layer Transition on a Naca Airfoil

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F22%3A00533371" target="_blank" >RIV/61388998:_____/22:00533371 - isvavai.cz</a>

Výsledek na webu

<a href="https://www.e3s-conferences.org/articles/e3sconf/pdf/2022/12/e3sconf_mtt2022_01011.pdf" target="_blank" >https://www.e3s-conferences.org/articles/e3sconf/pdf/2022/12/e3sconf_mtt2022_01011.pdf</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1051/e3sconf/202234501011" target="_blank" >10.1051/e3sconf/202234501011</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Optical and Hot-Film Measurements of the Boundary Layer Transition on a Naca Airfoil

Popis výsledku v původním jazyce

This study explores the possibilities of identifying position of a boundary layer transition using hot film measurements complemented by classical optical methods i.e. interferometry and schlieren method. The subject of the measurement is a NACA 0010-64 airfoil with varying leading edge surface quality corresponding to smooth surface and rough surface with Ra ~ 50 and Ra ~ 100. Measurements are performed at several subsonic regimes and a transonic regime.nDespite several shortcomings of the experimental setup, the method proved to be useful in providing information on the boundary layer transition. Measurements show that in the case of smooth leading edge, the onset of the boundary layer transition shifts upstream with increasing inlet Mach number and the major portion of the boundary layer is transitional. This is in accordance with other published results on the boundary layer transition on this kind of airfoils [1]. In all cases with the rough leading edge, the complete transition takes place on the rough portion of the surface already.n

Název v anglickém jazyce

Optical and Hot-Film Measurements of the Boundary Layer Transition on a Naca Airfoil

Popis výsledku anglicky

This study explores the possibilities of identifying position of a boundary layer transition using hot film measurements complemented by classical optical methods i.e. interferometry and schlieren method. The subject of the measurement is a NACA 0010-64 airfoil with varying leading edge surface quality corresponding to smooth surface and rough surface with Ra ~ 50 and Ra ~ 100. Measurements are performed at several subsonic regimes and a transonic regime.nDespite several shortcomings of the experimental setup, the method proved to be useful in providing information on the boundary layer transition. Measurements show that in the case of smooth leading edge, the onset of the boundary layer transition shifts upstream with increasing inlet Mach number and the major portion of the boundary layer is transitional. This is in accordance with other published results on the boundary layer transition on this kind of airfoils [1]. In all cases with the rough leading edge, the complete transition takes place on the rough portion of the surface already.n

Druh

D - Stať ve sborníku

CEP obor

—

OECD FORD obor

20302 - Applied mechanics

Projekt

<a href="/cs/project/TH02020057" target="_blank" >TH02020057: Profilové turbínové mříže pro supersonická proudová pole</a><br>

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2022

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název statě ve sborníku

E3S Web of Conferences

ISBN

—

ISSN

2267-1242

e-ISSN

2267-1242

Počet stran výsledku

9

Strana od-do

01011

Název nakladatele

EDP Sciences

Místo vydání

Cedex A

Místo konání akce

Santorini

Datum konání akce

21. 9. 2020

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

—