DESIGN OF PRECISION AERODYNAMIC BALANCE AND LOW SPEED WIND TUNNEL TESTING FOR UNMANNED AERIAL VEHICLES AIRFOILS

Kód výsledku v IS VaVaI

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Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

DESIGN OF PRECISION AERODYNAMIC BALANCE AND LOW SPEED WIND TUNNEL TESTING FOR UNMANNED AERIAL VEHICLES AIRFOILS

Popis výsledku v původním jazyce

This paper presents the design and validation of a measurement system for aerodynamic characteristics of unmanned aerial vehicles. An aerodynamic balance was designed in order to measure the lift, drag forces and pitching moment for different airfoils. Wind tunnel tests of a two dimensional NACA four digits family airfoil and four different modifications of this airfoil were performed to validate the aerodynamic measurement system. The modification of this airfoil was made in order to create a blowing outlet with the shape of a step on the suction surface. This analysis involved the aerodynamic performance, obtaining lift, drag and pitching moment coefficients curves as a function of the angle of attack experimentally for the no blowing condition, by means of wind tunnel tests. Finally, results of the wind tunnel tests were compared with numerical results obtained by means of computational fluid dynamics as well as with other experimental references and found to be in good agreement.

Název v anglickém jazyce

DESIGN OF PRECISION AERODYNAMIC BALANCE AND LOW SPEED WIND TUNNEL TESTING FOR UNMANNED AERIAL VEHICLES AIRFOILS

Popis výsledku anglicky

This paper presents the design and validation of a measurement system for aerodynamic characteristics of unmanned aerial vehicles. An aerodynamic balance was designed in order to measure the lift, drag forces and pitching moment for different airfoils. Wind tunnel tests of a two dimensional NACA four digits family airfoil and four different modifications of this airfoil were performed to validate the aerodynamic measurement system. The modification of this airfoil was made in order to create a blowing outlet with the shape of a step on the suction surface. This analysis involved the aerodynamic performance, obtaining lift, drag and pitching moment coefficients curves as a function of the angle of attack experimentally for the no blowing condition, by means of wind tunnel tests. Finally, results of the wind tunnel tests were compared with numerical results obtained by means of computational fluid dynamics as well as with other experimental references and found to be in good agreement.

Druh

D - Stať ve sborníku

CEP obor

BK - Mechanika tekutin

OECD FORD obor

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Projekt

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Návaznosti

S - Specificky vyzkum na vysokych skolach

Rok uplatnění

2010

Kód důvěrnosti údajů

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

Název statě ve sborníku

21st International Symposium on Transport Phenomena

ISBN

978-986-6184-25-3

ISSN

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e-ISSN

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Počet stran výsledku

1

Strana od-do

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Název nakladatele

Tsang Hai Book Publishing, Co

Místo vydání

Taichung, Taiwan 11F Chungkang Road Sec 122-19

Místo konání akce

Kaohsiung

Datum konání akce

2. 11. 2010

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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