Experimental and numerical study of turbulent flow around a Fanwings profile

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26110%2F19%3APU132715" target="_blank" >RIV/00216305:26110/19:PU132715 - isvavai.cz</a>

Výsledek na webu

<a href="http://www.tandfonline.com/doi/full/10.1080/19942060.2019.1639076" target="_blank" >http://www.tandfonline.com/doi/full/10.1080/19942060.2019.1639076</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1080/19942060.2019.1639076" target="_blank" >10.1080/19942060.2019.1639076</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Experimental and numerical study of turbulent flow around a Fanwings profile

Popis výsledku v původním jazyce

The main objective of this paper is an experimental and numerical study of airflow on a propulsive wing also called ventilated wing or FANWING, which is a drone operating at low speed. To optimize the aerodynamic shape of the Fanwing, two different configurations of NACA4415 rectangular wing profile were realized. The first one is a wing where the Cross-Flow Fan is fitted directly to the leading edge with a classic niche. For the second one, we truncated the extension of the niche to create a profile without nose. Two flow velocities with constant fan rotation were used and observed in the range of −16° < α < +30°. A lift coefficient generated by the profiles increases and the drag coefficient decreases, while the distribution of the pressure coefficient on the upper surface increases abruptly because of the flow recirculation. The experiment was performed in a subsonic wind tunnel TE44 and numerical simulations in software Fluent 6.3.2.6. Both approaches are in good agreement. The visualization showed that the recirculation phenomenon occurs right after the discharge of the cross-flow fan. It reveals that the jet coming out of the fan causes a strong wake behind the profile and suppresses the boundary layer separation.

Název v anglickém jazyce

Experimental and numerical study of turbulent flow around a Fanwings profile

Popis výsledku anglicky

The main objective of this paper is an experimental and numerical study of airflow on a propulsive wing also called ventilated wing or FANWING, which is a drone operating at low speed. To optimize the aerodynamic shape of the Fanwing, two different configurations of NACA4415 rectangular wing profile were realized. The first one is a wing where the Cross-Flow Fan is fitted directly to the leading edge with a classic niche. For the second one, we truncated the extension of the niche to create a profile without nose. Two flow velocities with constant fan rotation were used and observed in the range of −16° < α < +30°. A lift coefficient generated by the profiles increases and the drag coefficient decreases, while the distribution of the pressure coefficient on the upper surface increases abruptly because of the flow recirculation. The experiment was performed in a subsonic wind tunnel TE44 and numerical simulations in software Fluent 6.3.2.6. Both approaches are in good agreement. The visualization showed that the recirculation phenomenon occurs right after the discharge of the cross-flow fan. It reveals that the jet coming out of the fan causes a strong wake behind the profile and suppresses the boundary layer separation.

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

—

OECD FORD obor

20101 - Civil engineering

Projekt

—

Návaznosti

S - Specificky vyzkum na vysokych skolach

Rok uplatnění

2019

Kód důvěrnosti údajů

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

Název periodika

Engineering Applications of Computational Fluid Mechanics

ISSN

1994-2060

e-ISSN

1997-003X

Svazek periodika

13

Číslo periodika v rámci svazku

1

Stát vydavatele periodika

CN - Čínská lidová republika

Počet stran výsledku

5

Strana od-do

698-712

Kód UT WoS článku

000476481800001

EID výsledku v databázi Scopus

2-s2.0-85069452584