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
Aerodynamic Measurement Technology and Ground Testing ; 2000 ; Denver, CO, United States
2000-01-01
Preprint
Keine Angabe
Englisch
Simultaneous Luminescence Pressure and Temperature Measurement System for Hypersonic Wind Tunnels
Online Contents | 1995
|Springer Verlag | 2020
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