Abstract
Temperature-sensitive paint technique was applied to high-enthalpy shock tunnel JAXA-HIEST. The test model was circular cone model with the total length of 1100 mm. The model was equipped with thermocouples, and Temperature-Sensitive Paint was painted on the side of the model. Measured heat flux distributions were compared between Temperature-Sensitive Paint and thermocouples to evaluate temperature-sensitive paint measurement in High-Enthalpy Shock Tunnel. Near the end of the test model, the trend that heat flux increase with the distance from nosetip was same in two measurement techniques. Temperature-Sensitive Paint could detect the locations of boundary-layer transition. Furthermore, heat flux measurement quantitatively showed good agreement with the thermocouple measurement result by using in situ calibration.
This is a preview of subscription content, log in via an institution to check access.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
References
T. Liu, J.S. Sullivan, Pressure and Temperature Sensitive Paints (Springer, Berlin, 2005)
K. Nakakita, T. Osafune, K. Asai, Global heat transfer measurement in a hypersonic shock tunnel using temperature-sensitive paint, in 41st Aerospace Sciences Meeting and Exhibit, AIAA-2003-0743, 2003
Y. Ishiguro, H. Nagai, K. Asai, K. Nakakita, Visualization of hypersonic compression corner flows using temperature and pressure-sensitive paints, in 45th AIAA Aerospace Sciences Meeting and Exhibit, AIAA-2007-118, 2007
T. Horagiri, H. Nagai, Development of Temperature-Sensitive Paint with High Performance and Responsivity for Aerodynamic Heating Measurement, AIAA 2014–1408, 2014
H. Nagai, T. Horagiri, H. Tanno, T. Komuro, Visualization of a re-entry vehicle in hypersonic flow using temperature -sensitive paint, in Proceedings of 16th International Symposium on Flow Visualization, ISFV16-1275, 2014
K. Itoh, S. Ueda, H. Tanno, T. Komuro, K. Sato, Hypersonic aerothermodynamic and scramjet research using high enthalpy shock tunnel. Shock Waves 12, 93–98 (2002)
Author information
Authors and Affiliations
Corresponding author
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 2019 Springer International Publishing AG, part of Springer Nature
About this paper
Cite this paper
Nagai, H., Nagayama, T., Tanno, H., Komuro, T. (2019). Boundary-Layer Transition Detection at High-Enthalpy Flow Using Temperature-Sensitive Paint. In: Sasoh, A., Aoki, T., Katayama, M. (eds) 31st International Symposium on Shock Waves 1. ISSW 2017. Springer, Cham. https://doi.org/10.1007/978-3-319-91020-8_51
Download citation
DOI: https://doi.org/10.1007/978-3-319-91020-8_51
Published:
Publisher Name: Springer, Cham
Print ISBN: 978-3-319-91019-2
Online ISBN: 978-3-319-91020-8
eBook Packages: EngineeringEngineering (R0)