Cryogenic pressure sensitive fluorescent paint systems

Richard G. Erausquin; Corey T. Cunnigham; John P. Sullivan; Keisuke Asai; Hiroshi Kanda; Tetsuya Kunimasu; Yoshimi Lijima

Cryogenic pressure sensitive fluorescent paint systems

Richard G. Erausquin, Corey T. Cunnigham, John P. Sullivan, Keisuke Asai, Hiroshi Kanda, Tetsuya Kunimasu, Yoshimi Lijima

Research output: Contribution to conference › Paper › peer-review

10 Citations (Scopus)

Abstract

In recent experiments, we demonstrated the feasibility of using luminescent coatings for surface pressure measurement in a cryogenic wind tunnel. Numerous PSP samples were calibrated and a new coating technology in which luminescent molecules are directly deposited onto an anodized aluminum model surface was developed. The resulting coating has an extremely high oxygen sensitivity for mole fractions of oxygen less than 0.1%. Cryogenic pressure calibration techniques are discussed and calibration curves presented. 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 (250 PPM)in the test gas was kept constant. The results using an in situ calibration for the paintderived pressure distributions are in good agreement with pressure tap measurements.

Original language	English
Publication status	Published - 1998 Jan 1
Externally published	Yes
Event	36th AIAA Aerospace Sciences Meeting and Exhibit, 1998 - Reno, United States Duration: 1998 Jan 12 → 1998 Jan 15

Other

Other	36th AIAA Aerospace Sciences Meeting and Exhibit, 1998
Country	United States
City	Reno
Period	98/1/12 → 98/1/15

ASJC Scopus subject areas

Engineering(all)
Space and Planetary Science

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title = "Cryogenic pressure sensitive fluorescent paint systems",

abstract = "In recent experiments, we demonstrated the feasibility of using luminescent coatings for surface pressure measurement in a cryogenic wind tunnel. Numerous PSP samples were calibrated and a new coating technology in which luminescent molecules are directly deposited onto an anodized aluminum model surface was developed. The resulting coating has an extremely high oxygen sensitivity for mole fractions of oxygen less than 0.1%. Cryogenic pressure calibration techniques are discussed and calibration curves presented. 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 (250 PPM)in the test gas was kept constant. The results using an in situ calibration for the paintderived pressure distributions are in good agreement with pressure tap measurements.",

author = "Erausquin, {Richard G.} and Cunnigham, {Corey T.} and Sullivan, {John P.} and Keisuke Asai and Hiroshi Kanda and Tetsuya Kunimasu and Yoshimi Lijima",

year = "1998",

month = jan,

day = "1",

language = "English",

note = "36th AIAA Aerospace Sciences Meeting and Exhibit, 1998 ; Conference date: 12-01-1998 Through 15-01-1998",

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TY - CONF

T1 - Cryogenic pressure sensitive fluorescent paint systems

AU - Erausquin, Richard G.

AU - Cunnigham, Corey T.

AU - Sullivan, John P.

AU - Asai, Keisuke

AU - Kanda, Hiroshi

AU - Kunimasu, Tetsuya

AU - Lijima, Yoshimi

PY - 1998/1/1

Y1 - 1998/1/1

N2 - In recent experiments, we demonstrated the feasibility of using luminescent coatings for surface pressure measurement in a cryogenic wind tunnel. Numerous PSP samples were calibrated and a new coating technology in which luminescent molecules are directly deposited onto an anodized aluminum model surface was developed. The resulting coating has an extremely high oxygen sensitivity for mole fractions of oxygen less than 0.1%. Cryogenic pressure calibration techniques are discussed and calibration curves presented. 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 (250 PPM)in the test gas was kept constant. The results using an in situ calibration for the paintderived pressure distributions are in good agreement with pressure tap measurements.

AB - In recent experiments, we demonstrated the feasibility of using luminescent coatings for surface pressure measurement in a cryogenic wind tunnel. Numerous PSP samples were calibrated and a new coating technology in which luminescent molecules are directly deposited onto an anodized aluminum model surface was developed. The resulting coating has an extremely high oxygen sensitivity for mole fractions of oxygen less than 0.1%. Cryogenic pressure calibration techniques are discussed and calibration curves presented. 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 (250 PPM)in the test gas was kept constant. The results using an in situ calibration for the paintderived pressure distributions are in good agreement with pressure tap measurements.

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T2 - 36th AIAA Aerospace Sciences Meeting and Exhibit, 1998

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