Surface pressure measurement in a cryogenic wind tunnel by using luminescent coating

Keisuke Asai, Hiroshi Kanda, Corey T. Cunningham, Rick Erausquin, John P. Sullivan

研究成果: Article査読

69 被引用数 (Scopus)

抄録

In recent experiments, we demonstrated the feasibility of using luminescent coatings for surface pressure measurement in a cryogenic wind tunnel. This technique is based on a new coating technology in which luminescent molecules are directly deposited onto the model surface by an electrochemical process. The resulting coating has an extremely high oxygen sensitivity for mole fractions of oxygen is less than 0.1%. This capability allows us to measure the pressure field on the model surface in a cryogenic wind tunnel. To demonstrate this technology, a 14%-thick bump model was tested in the 0.1-m Transonic Cryogenic Wind Tunnel at NAL. Mach number was changed from 0.4 to 0.84 whereas temperature was maintained at 100 K. A small amount of oxygen was injected into the tunnel and the mole fraction of oxygen in the test gas was kept constant. We acquired two intensity images, one taken at low speeds and the other taken at high Mach numbers. By taking the ratio of these images, surface pressure distributions on the model were clearly captured. The result of the in situ calibration showed that effects of temperature dependence of the coating was negligible. The paint-derived pressure distributions are in good agreement with pressure tap measurements.

本文言語English
ページ(範囲)105-110
ページ数6
ジャーナルICIASF Record, International Congress on Instrumentation in Aerospace Simulation Facilities
1997
出版ステータスPublished - 1997 12 1
外部発表はい

ASJC Scopus subject areas

  • 器械工学
  • 航空宇宙工学
  • 凝縮系物理学

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