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

Result code in IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F10%3A00171960" target="_blank" >RIV/68407700:21220/10:00171960 - isvavai.cz</a>
Result on the web
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DOI - Digital Object Identifier
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Result language
angličtina
Original language name
DESIGN OF PRECISION AERODYNAMIC BALANCE AND LOW SPEED WIND TUNNEL TESTING FOR UNMANNED AERIAL VEHICLES AIRFOILS
Original language description
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.
Czech name
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Czech description
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Publication year
2010
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Article name in the collection
21st International Symposium on Transport Phenomena
ISBN
978-986-6184-25-3
ISSN
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e-ISSN
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Number of pages
1
Pages from-to
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Publisher name
Tsang Hai Book Publishing, Co
Place of publication
Taichung, Taiwan 11F Chungkang Road Sec 122-19
Event location
Kaohsiung
Event date
Nov 2, 2010
Type of event by nationality
WRD - Celosvětová akce
UT code for WoS article
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