Proceedings ArticleDOI
Surface temperature/heat transfer measurement using a quantitative phosphor thermography system
G. M. Buck
- Vol. 29
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TLDR
A relative intensity phosphor thermography technique developed for surface heating studies in hypersonic wind tunnels is described in this article, where a direct relationship between relative emission intensity and phosphor temperature is used for quantitative surface temperature measurements in time.Abstract:
A relative-intensity phosphor thermography technique developed for surface heating studies in hypersonic wind tunnels is described. A direct relationship between relative emission intensity and phosphor temperature is used for quantitative surface temperature measurements in time. The technique provides global surface temperature-time histories using a 3-CCD (Charge Coupled Device) video camera and digital recording system. A current history of technique development at Langley is discussed. Latest developments include a phosphor mixture for a greater range of temperature sensitivity and use of castable ceramics for inexpensive test models. A method of calculating surface heat-transfer from thermal image data in blowdown wind tunnels is included in an appendix, with an analysis of material thermal heat-transfer properties. Results from tests in the Langley 31-Inch Mach 10 Tunnel are presented for a ceramic orbiter configuration and a four-inch diameter hemisphere model. Data include windward heating for bow-shock/wing-shock interactions on the orbiter wing surface, and a comparison with prediction for hemisphere heating distribution.read more
Citations
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Book ChapterDOI
Advances in Heat Flux Measurements
TL;DR: The focus of this chapter is on the newer techniques and novel uses of the older techniques developed and applied in the last 10 to 20 years, which have greatly increased the resolution and operating range of heat-flux instrumentation.
Journal ArticleDOI
Hypersonic Boundary-Layer Trip Development for Hyper-X
TL;DR: In this article, boundary-layer trip devices for the Hyper-X forebody have been experimentally examined in several wind tunnels, including the NASALangleyResearch Center 20-Inch Mach 6 Air and 31-inch Mach 10 Air tunnels and in the HYPULSE Reeected Shock Tunnel at the General Applied Sciences Laboratory.
Journal ArticleDOI
Global Aeroheating Wind-Tunnel Measurements Using Improved Two-Color Phosphor Thermography Method
TL;DR: In this paper, a weighted two-color relative intensity e uorescence theory for quantitatively determining surface temperatures on hypersonic wind-tunnel models and an improved application of the one-dimensional conduction theory for use in determining global heating mappings is described.
Journal ArticleDOI
X-33 Hypersonic Boundary-Layer Transition
TL;DR: In this article, the effects of discrete and distributed roughness elements on boundary layer transition, which included trip height, size, location, and distribution, both on and off the windward centerline, were investigated.
Proceedings ArticleDOI
Reduction and Analysis of Phosphor Thermography Data With the IHEAT Software Package
TL;DR: In this paper, the IHEAT software package is used for the efficient data reduction and analysis of the NASA Langley Research Center's (LaRC) two-color relative-intensity phosphor thermography method.
References
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Proceedings ArticleDOI
Langley hypersonic aerodynamic/aerothermodynamic testing capabilities - Present and future
TL;DR: The Langley Hypersonic Facility Complex consists of nine hypersonic, blowdown-to-vacuum wind tunnels that complement one another to provide a range of Mach number from 6 to 22, with Reynolds number from 0.03 to 40 million per foot and, most importantly for blunt configurations, a normal shock density ratio from 4 to 12 as mentioned in this paper.
Journal ArticleDOI
High resolution digital flowfield imaging of jets
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Proceedings ArticleDOI
Experimental heating distributions for biconics at incidence in Mach 10 air and comparison to prediction
TL;DR: In this article, a 1.9 percent scale model of a generic, aero-assisted vehicle proposed for missions to a number of planets and also a candidate as a moderate L/D earth orbital transfer vehicle was measured on a model of the Space Station.