Boundary-layer transition detection in a cryogenic wind tunnel using luminescent paint

Keisuke Asai, Hiroshi Kanda, Tetsuya Kunimasu, Tianshu Liu, John P. Sullivan

研究成果: Article査読

48 被引用数 (Scopus)


A technique for boundary-layer transition detection in a cryogenic wind tunnel has been developed. This technique is based on the thermal quenching of luminescent molecules. Calibration results show that luminescence of the paint composed of ruthenium complex and silicone polymer is strongly sensitive to temperatures over the range of 90-220 K. This capability allows one to visualize thermal signatures across the boundary-layer transition. A thin paint coating has been applied on three airfoil models with different thermal insulation properties. The paint was excited by a xenon light and the luminescence image was acquired using a high-resolution digital camera. To enhance the surface temperature signatures between laminar and turbulent regions, either the flow or the model substrate was cooled or heated in an active manner. Transition patterns have been successfully visualized by processing the luminescent images. Boundary-layer transition has been detected by using this technique over a cryogenic temperature range of 90-150 K in subsonic and transonic flows.

ジャーナルJournal of Aircraft
出版ステータスPublished - 1997

ASJC Scopus subject areas

  • 航空宇宙工学


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