Year: 2005
Type: conference-paper
Abstract: The work described here relates to the method measuring the boundary layer transition at large-scale and low-speed wind tunnel. The objective of the research is to improve the test technique and to know a precise procedure about transition measurements, especially for an aircraft model at such type of wind tunnel. At JAXA 6.5 m x 5.5 m Low-Speed Wind Tunnel (LWT1), the boundary layer growing on the left-wing of the ONERA-Model was investigated using two kinds of the quantitative methods (Preston Tube and Hotfilm Sensor) and also two kinds of the visualizing methods (Temperature-Sensitive Liquid Crystal, Infrared Camera). Throughout the experiment, a lot of knowledge were obtained. Transition points investigated by four kinds of methods were correctively agreed.
Authors: 横川, 譲, 青木, 良尚, 森田, 義郎, 高橋, ひとし, 星野, 秀雄, 室田, 勝一, 野中, 修, 真城, 仁, 遠藤, 亮, 吉田, 憲司, Aoki, Yoshinao, Morita, Yoshio, Mashiro, Jin, Endo, Atsushi
Language: Japanese
Subfield: Computational Mechanics
Field: Engineering
Domain: Physical Sciences
Open Access status: green
OpenAlex ID: W7207995151