| タイトル | Pressure- and Temperature-Sensitive Paint at 0.3-m Transonic Cryogenic Tunnel |
| 本文（外部サイト） | http://hdl.handle.net/2060/20150018920 |
| 著者（英） | Watkins, A. Neal; Lipford, William E.; Goodman, Kyle Z.; Leighty, Bradley D. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2015-09-01 |
| 言語 | eng |
| 内容記述 | Recently both Pressure- and Temperature-Sensitive Paint experiments were conducted at cryogenic conditions in the 0.3-m Transonic Cryogenic Tunnel at NASA Langley Research Center. This represented a re-introduction of the techniques to the facility after more than a decade, and provided a means to upgrade the measurements using newer technology as well as demonstrate that the techniques were still viable in the facility. Temperature-Sensitive Paint was employed on a laminar airfoil for transition detection and Pressure-Sensitive Paint was employed on a supercritical airfoil. This report will detail the techniques and their unique challenges that need to be overcome in cryogenic environments. In addition, several optimization strategies will also be discussed. |
| NASA分類 | Instrumentation and Photography |
| レポートNO | L-20601
NASA/TM-2015-218801
NF1676L-22330 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
