Spatial growth of the spanwise disturbance induced by a synthetic jet on separation control over an airfoil

研究成果: Conference contribution

抄録

The spatial growth of the spanwise disturbance induced by a synthetic jet is investigated on separated-flow control around NACA0015 (Re=63; 000 and AOA = 12: 0°) using a large-eddy simulation. The synthetic jet is installed at a leading edge which is numerically modeled by a three-dimensional deforming cavity: “Cavity model”; and an artificial jet profile for a boundary condition: “Bc model”. The jet profile of the Bc model is assumed to be sinusoidally oscillated in a spanwise direction with a wave number from kyin=2π = 0 to 95. In the Cavity model case, the modes around ky=2π= 20 to 30 are selectively amplified near the synthetic jet, which remains also in the turbulent boundary layer. In the Bc model cases, the most quick turbulent transition occurs in the case with kyin=2π = 30, where the coherent spanwise mode strongly remains in the turbulent boundary layer although its aerodynamic performance is not best. This result indicates that in the present condition, the spanwise disturbance of the jet profile does not always contribute to the higher aerodynamic performance even if it provides smooth and quick turbulent transition.

本文言語English
ホスト出版物のタイトル53rd AIAA Aerospace Sciences Meeting
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN(印刷版)9781624103438
DOI
出版ステータスPublished - 2015 1 1
外部発表はい
イベント53rd AIAA Aerospace Sciences Meeting, 2015 - Kissimmee, United States
継続期間: 2015 1 52015 1 9

出版物シリーズ

名前53rd AIAA Aerospace Sciences Meeting

Other

Other53rd AIAA Aerospace Sciences Meeting, 2015
国/地域United States
CityKissimmee
Period15/1/515/1/9

ASJC Scopus subject areas

  • 航空宇宙工学

フィンガープリント

「Spatial growth of the spanwise disturbance induced by a synthetic jet on separation control over an airfoil」の研究トピックを掘り下げます。これらがまとまってユニークなフィンガープリントを構成します。

引用スタイル