Experimental investigation of 3D shock / boundary layer interaction control in transonic flows

H. Ogawa, H. Babinsky

研究成果: Chapter in Book/Report/Conference proceedingConference contribution

6 被引用数 (Scopus)

抄録

A novel supersonic wind tunnel setup is proposed to enable the investigation of control on a normal shock wave. Previous experimental arrangements were found to suffer from shock instability. Wind tunnel tests with and without control have confirmed the capability of the new setup to stabilise a shock structure at a target position without changing the nature of the shock wave / boundary layer interaction flow at M = 1.3 and M = 1.5. Flow visualisation and pressure measurements with the new setup have revealed detailed characteristics of shock wave / boundary layer interactions and a λ-shock structure as well as benefits of control in total drag reduction in the presence of 3D bump control.

本文言語英語
ホスト出版物のタイトルCollection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
ページ10486-10497
ページ数12
出版ステータス出版済み - 12 1 2006
外部発表はい
イベント44th AIAA Aerospace Sciences Meeting 2006 - Reno, NV, 米国
継続期間: 1 9 20061 12 2006

出版物シリーズ

名前Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
14

会議

会議44th AIAA Aerospace Sciences Meeting 2006
国/地域米国
CityReno, NV
Period1/9/061/12/06

All Science Journal Classification (ASJC) codes

  • 宇宙惑星科学
  • 航空宇宙工学

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