Other
Scientific paper
Feb 2005
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2005esasp.563...57k&link_type=abstract
Proceedings of the Fifth European Symposium on Aerothermodynamics for Space Vehicles (ESA SP-563). 8-11 November 2004, Cologne,
Other
Scientific paper
A study has been conducted to measure surface temperatures inside a model rectangular supersonic combustor using a non-intrusive thermal imaging system, based on the fluorescence properties of a dysprosium doped yttrium-aluminum-garnet (Dy3+ :YAG) thermographic phosphor. The wind tunnel was a blow-down type using vitiated air with nominal conditions at the entrance of the test section M∞=2.5, Po=5x105 N/m2 , To=800 K and Re∞/m=9.6x106 . Fuel was hydrogen gas at room temperature injected parallel to the tunnel through a fuel injector slit located along the backward surface of a step. The results under hot flow conditions were compared with numerical simulations performed using a 2-D Navier-Stokes code with full chemistry. Nomenclature h height of backward facing step L coating thickness M Mach number P pressure q heat flux Re Reynolds number T temperature t time x horizontal direction y vertical direction y* semi-infinity penetration depth κ thermal conductivity µ dynamic viscosity Subscripts and Superscripts ini initial o total condition sub substrate tsp temperature sensitive paint w wall x horizontal direction ∞ infinity
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