Effect of Flow Parameters Variation on Flutter Boundary of Benchmark Supercritical Wing

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F18%3APU129267" target="_blank" >RIV/00216305:26210/18:PU129267 - isvavai.cz</a>

Výsledek na webu

<a href="https://arc.aiaa.org/doi/abs/10.2514/1.J056913" target="_blank" >https://arc.aiaa.org/doi/abs/10.2514/1.J056913</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.2514/1.J056913" target="_blank" >10.2514/1.J056913</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Effect of Flow Parameters Variation on Flutter Boundary of Benchmark Supercritical Wing

Popis výsledku v původním jazyce

This paper presents a study of the flutter characteristics of the benchmark supercritical wing. The wing is rigid, and the aeroelastic behavior is modeled by a mounting called the pitch and plunge apparatus. It allows the wing to move in a vertical direction and rotate around a pivot point. The simulations are performed using a high-fidelity computational fluid dynamics code coupled to a linear structural solver. The three major objectives of the presented work are the evaluation of the effect of a gas composition, a Reynolds number, and an angle of attack on a flutter boundary at subsonic and transonic Mach numbers. The gas composition effect is evaluated using R-12 coolant gas and air. The angle of attack is varied between 0 and 5 deg, thus covering both attached and separated flows.

Název v anglickém jazyce

Effect of Flow Parameters Variation on Flutter Boundary of Benchmark Supercritical Wing

Popis výsledku anglicky

This paper presents a study of the flutter characteristics of the benchmark supercritical wing. The wing is rigid, and the aeroelastic behavior is modeled by a mounting called the pitch and plunge apparatus. It allows the wing to move in a vertical direction and rotate around a pivot point. The simulations are performed using a high-fidelity computational fluid dynamics code coupled to a linear structural solver. The three major objectives of the presented work are the evaluation of the effect of a gas composition, a Reynolds number, and an angle of attack on a flutter boundary at subsonic and transonic Mach numbers. The gas composition effect is evaluated using R-12 coolant gas and air. The angle of attack is varied between 0 and 5 deg, thus covering both attached and separated flows.

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

—

OECD FORD obor

20304 - Aerospace engineering

Projekt

<a href="/cs/project/LO1202" target="_blank" >LO1202: NETME CENTRE PLUS</a><br>

Návaznosti

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

Rok uplatnění

2018

Kód důvěrnosti údajů

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

Název periodika

AIAA JOURNAL

ISSN

0001-1452

e-ISSN

1533-385X

Svazek periodika

57

Číslo periodika v rámci svazku

2

Stát vydavatele periodika

US - Spojené státy americké

Počet stran výsledku

10

Strana od-do

772-781

Kód UT WoS článku

000459634700010

EID výsledku v databázi Scopus

2-s2.0-85067501020