TY - GEN
T1 - Global heat flux measurement using temperature-sensitive paint in high-enthalpy shock tunnel HIEST
AU - Nagayama, Takehiro
AU - Nagai, Hiroki
AU - Tanno, Hideyuki
AU - Komuro, Tomoyuki
N1 - Funding Information:
The authors would like to thank Mr. Kazuo Sato, Mr. Takuya Maehara and all members of HIEST section, Kakuda Space Center, JAXA for their kind preparation and operation of the wind tunnel test and measurement. The authors are indebted to Mr. Tomoaki Narita, Mr. Kentaro Fujimura and Ms. Yoshiko Hatakeyama, Japan Aerospace Technology Foundation for their valuable support regarding the measurements and operation.
Publisher Copyright:
© 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2017
Y1 - 2017
N2 - A TSP (Temperature-Sensitive Paint) measurement technique was applied to high enthalpy shock tunnel JAXA-HIEST in Japan. Circular cone model with the total length of 1100 mm was used as a test model. The model was equipped with thermocouples, and TSP was painted on the side of the model. Measured heat flux distributions by TSP were compared with that by thermocouples to evaluate TSP measurement in JAXA-HIEST. In this test, TSP heat flux measurement could detect the boundary layer transition, and the heat flux profiles along the centerline from the nosetip to the rear showed almost same tendency by two different measurement techniques. In addition, when in-situ calibration of TSP is employed, heat flux profiles along the model centerline obtained by TSP wan in good agreement with thermocouples quantitatively at low stagnation enthalpy condition of H0 = 4.0 MJ/kg. However, the heat flux measured by TSP with a-priori calibration was made smaller than that of thermocouples due to the self-illumination of test flow. In a test conducted at the stagnation enthalpy of 5.0 MJ/kg, self-illumination of flow become too prominent to carry out quantitative TSP measurement. To achieve accurate quantitative heat flux measurement by TSP in HIEST, development of a measurement system which can remove the illumination from the flow is required.
AB - A TSP (Temperature-Sensitive Paint) measurement technique was applied to high enthalpy shock tunnel JAXA-HIEST in Japan. Circular cone model with the total length of 1100 mm was used as a test model. The model was equipped with thermocouples, and TSP was painted on the side of the model. Measured heat flux distributions by TSP were compared with that by thermocouples to evaluate TSP measurement in JAXA-HIEST. In this test, TSP heat flux measurement could detect the boundary layer transition, and the heat flux profiles along the centerline from the nosetip to the rear showed almost same tendency by two different measurement techniques. In addition, when in-situ calibration of TSP is employed, heat flux profiles along the model centerline obtained by TSP wan in good agreement with thermocouples quantitatively at low stagnation enthalpy condition of H0 = 4.0 MJ/kg. However, the heat flux measured by TSP with a-priori calibration was made smaller than that of thermocouples due to the self-illumination of test flow. In a test conducted at the stagnation enthalpy of 5.0 MJ/kg, self-illumination of flow become too prominent to carry out quantitative TSP measurement. To achieve accurate quantitative heat flux measurement by TSP in HIEST, development of a measurement system which can remove the illumination from the flow is required.
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U2 - 10.2514/6.2017-1682
DO - 10.2514/6.2017-1682
M3 - Conference contribution
AN - SCOPUS:85017254227
T3 - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
BT - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 55th AIAA Aerospace Sciences Meeting
Y2 - 9 January 2017 through 13 January 2017
ER -