Numerical modelling of plasma for flow control in aerospace applications

Author

Konstantinos, K. ; Rogier, F. ; Boeuf, J.

Author_Institution

DTIM, ONERA, Berlin, France

fYear

2012

fDate

8-13 July 2012

Abstract

A crucial aspect for supersonic flights is the strong shock wave that forms in front of the air vehicle. By modifying the supersonic incoming flow, one can adjust this wave -which is the most contributing factor of the drag coefficient of an aircraft- and have consequently positive effects on the fuel consumption and on the noise produced by the object due to the sonic boom. Lately, plasma associated flow control actuators have been in the center of flow control research and especially of supersonic applications.

Keywords

actuators; aerodynamics; aircraft; drag; flow control; noise; numerical analysis; plasma applications; plasma simulation; shock waves; supersonic flow; aerospace applications; air vehicle front; aircraft drag coefficient factor; fuel consumption; noise; plasma associated flow control actuators; plasma numerical modelling; positive effects; shock wave; sonic boom; supersonic applications; supersonic flights; supersonic incoming flow; Atmospheric modeling; Mathematical model; Numerical models; Plasmas; Shock waves; Surface waves; Uninterruptible power systems;

fLanguage

English

Publisher

ieee

Conference_Titel

Plasma Science (ICOPS), 2012 Abstracts IEEE International Conference on

Conference_Location

Edinburgh

ISSN

0730-9244

Print_ISBN

978-1-4577-2127-4

Electronic_ISBN

0730-9244

Type

conf

DOI

10.1109/PLASMA.2012.6383756

Filename

6383756