An Analytically Calculated Drag of an Aircraft with Ducted Fan Propulsion Unit in Correlation with Results of an Experiment in Wind Tunnel

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F14%3A00217816" target="_blank" >RIV/68407700:21220/14:00217816 - isvavai.cz</a>

Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

An Analytically Calculated Drag of an Aircraft with Ducted Fan Propulsion Unit in Correlation with Results of an Experiment in Wind Tunnel

Popis výsledku v původním jazyce

This paper deals with description of results of an ultra-light aircraft with a ducted fan propulsion unit UL-39 fuselage drag measurements, which were performed in 3m aerodynamic tunnel in ARTE in Prague. Description of a fuselage measurement without propulsion unit is described at first and then a measurement with installed propulsion unit stopped and running. In both cases used methodology is described and comparison of experimentally determined values of fuselage drag and theoretically determined values is demonstrated. This comparison is intended mainly for verification of methodology used for prediction of drag of an aircraft with this nontraditional propulsion unit, which will lead to need of some methodology correction and extension before its next utilisation. Modification of used techniques will lead to accuracy improvement of required and available thrust prediction, which is necessary for next development of this aircraft. Those techniques can be applied as a methodology bac

Název v anglickém jazyce

An Analytically Calculated Drag of an Aircraft with Ducted Fan Propulsion Unit in Correlation with Results of an Experiment in Wind Tunnel

Popis výsledku anglicky

This paper deals with description of results of an ultra-light aircraft with a ducted fan propulsion unit UL-39 fuselage drag measurements, which were performed in 3m aerodynamic tunnel in ARTE in Prague. Description of a fuselage measurement without propulsion unit is described at first and then a measurement with installed propulsion unit stopped and running. In both cases used methodology is described and comparison of experimentally determined values of fuselage drag and theoretically determined values is demonstrated. This comparison is intended mainly for verification of methodology used for prediction of drag of an aircraft with this nontraditional propulsion unit, which will lead to need of some methodology correction and extension before its next utilisation. Modification of used techniques will lead to accuracy improvement of required and available thrust prediction, which is necessary for next development of this aircraft. Those techniques can be applied as a methodology bac

Druh

J_x - Nezařazeno - Článek v odborném periodiku (Jimp, Jsc a Jost)

CEP obor

JU - Aeronautika, aerodynamika, letadla

OECD FORD obor

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Projekt

<a href="/cs/project/FR-TI3%2F527" target="_blank" >FR-TI3/527: Ultralehký letoun s dmychadlovým pohonem</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2014

Kód důvěrnosti údajů

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

Název periodika

Czech Aerospace

ISSN

1211-877X

e-ISSN

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Svazek periodika

2014

Číslo periodika v rámci svazku

1

Stát vydavatele periodika

CZ - Česká republika

Počet stran výsledku

6

Strana od-do

26-31

Kód UT WoS článku

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EID výsledku v databázi Scopus

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