High-temperature luminescent coatings are being developed and applied for simultaneous pressure and temperature mapping in conventional-type hypersonic wind tunnels, providing global pressure as well as Global aeroheating measurements. Together, with advanced model fabrication and analysis methods, these techniques will provide a more rapid and complete experimental aerodynamic and aerothermodynamic database for future aerospace vehicles. The current status in development of simultaneous pressure- and temperature-sensitive coatings and measurement techniques for hypersonic wind tunnels at Langley Research Center is described. and initial results from a feasibility study in the Langley 31-Inch Mach 10 Tunnel are presented.
Simultaneous Global Pressure and Temperature Measurement Technique for Hypersonic Wind Tunnels
2000
14 pages
Report
No indication
English
Simultaneous Luminescence Pressure and Temperature Measurement System for Hypersonic Wind Tunnels
Online Contents | 1995
|Springer Verlag | 2020
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