Response Surface Method Application to High-Lift Configuration with Active Flow Control

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F12%3A%230001489" target="_blank" >RIV/00010669:_____/12:#0001489 - isvavai.cz</a>

Výsledek na webu

<a href="http://arc.aiaa.org/doi/pdf/10.2514/1.C031624" target="_blank" >http://arc.aiaa.org/doi/pdf/10.2514/1.C031624</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.2514/1.c031624" target="_blank" >10.2514/1.c031624</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Response Surface Method Application to High-Lift Configuration with Active Flow Control

Popis výsledku v původním jazyce

The use of Response Surface Method is presented and applied to the design of an Active Flow Control (AFC) for high-lift applications. The AFC is used for suppression of the flow separation on the slotted flap. The position, orientation, and continuous excitation characteristics of the actuator are set as design variables for the maximization of cost functions in landing configuration. The actuators are placed in the cove of the airfoil. The AFC is able to remove separation on the flap in this case completely. Subsequent verification of the efficiency of the optimum design, and possible energy saving, is done by an unsteady excitation. The unsteady excitation is simulated by periodic oscillatory pulse duty cycle. The influences of the excitation frequency and excitation time on the lift coefficient were examined. The frequency has almost no effect on CL. On the other hand, it has been found that the excitation time can be reduced by about 97% within one excitation period of duty cycle,

Název v anglickém jazyce

Response Surface Method Application to High-Lift Configuration with Active Flow Control

Popis výsledku anglicky

The use of Response Surface Method is presented and applied to the design of an Active Flow Control (AFC) for high-lift applications. The AFC is used for suppression of the flow separation on the slotted flap. The position, orientation, and continuous excitation characteristics of the actuator are set as design variables for the maximization of cost functions in landing configuration. The actuators are placed in the cove of the airfoil. The AFC is able to remove separation on the flap in this case completely. Subsequent verification of the efficiency of the optimum design, and possible energy saving, is done by an unsteady excitation. The unsteady excitation is simulated by periodic oscillatory pulse duty cycle. The influences of the excitation frequency and excitation time on the lift coefficient were examined. The frequency has almost no effect on CL. On the other hand, it has been found that the excitation time can be reduced by about 97% within one excitation period of duty cycle,

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

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Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2012

Kód důvěrnosti údajů

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

Název periodika

Journal of Aircraft

ISSN

0021-8669

e-ISSN

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Svazek periodika

49

Číslo periodika v rámci svazku

6

Stát vydavatele periodika

US - Spojené státy americké

Počet stran výsledku

7

Strana od-do

1796-1802

Kód UT WoS článku

000312764000021

EID výsledku v databázi Scopus

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