Open AccessSimultaneous global pressure and temperature measurement technique for hypersonic wind tunnels
Author(s) -
Gregory M. Buck
Publication year - 2000
Publication title -
nasa sti repository (national aeronautics and space administration)
Language(s) - English
Resource type - Conference proceedings
DOI - 10.2514/6.2000-2649
Subject(s) - hypersonic speed , temperature measurement , aerospace engineering , environmental science , pressure measurement , meteorology , atmospheric sciences , geology , physics , engineering , thermodynamics
SummaryPressure and temperature images were obtainedsimultaneously for the windward surface of anaerospace vehicle configuration in the 31-Inch Mach 10Air Tunnel at NASA Langley Research Center. Thesepreliminary results are at present qualitative. It isevident that the PTSC coating is stable throughout testsat the conditions of the Mach 10 tunnel for thisconfiguration and substrate material and can be furtheradjusted and calibrated to provide quantitative pressureand temperature data for future hypersonic wind tunnelexperiments. Coatings lor simultaneous global pressureand temperature measurements are still beingdeveloped.AcknowledgementsPaul Tucker of the Langley AerothermodynamicsSupport Section is gratefully acknowledged for hiscontributions to this work. particularly lbr his help inthe PTSC formula development and for coating andtesting of samples.ReferencesBuck, G. M., "An Imaging System for QuantitativeSurface Temperature Mapping Using Two-ColorThermographic Phosphors," ISA Paper 88-0772,May 1988.Buck, G. M., "Surface Temperature/Heat TransferMeasurement Using a Quantitative Phosphor4American Institute of Aeronautics and Astronautics
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