Stagnation Point Heat Transfer with Gas Injection Cooling

Details Stagnation Point Heat Transfer with Gas Injection Cooling Stagnation Point Heat Transfer with Gas Injection Cooling

Feb 2005

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2005esasp.563...75v&link_type=abstract

Proceedings of the Fifth European Symposium on Aerothermodynamics for Space Vehicles (ESA SP-563). 8-11 November 2004, Cologne,

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Scientific paper

The present paper deals with an experimental study of the stagnation-point heat transfer to a cooled copper surface with gas injection under subsonic conditions. Tests were made with a probe that combined a steady-state water-cooled calorimeter and that allows the capability to study convective blockage and to perform heat transfer measurements in presence of gas injection in the stagnation region. The copper probe was pierced by 52 holes, representing 2.4% of the total probe surface. The 1.2 MW high enthalpy plasma wind tunnel was operated at anode powers between 130 and 230 kW and a static pressures from 35 hPa up to 200 hPa. Air, carbon dioxide and argon were injected in the mass flow range 0-0.4 g/s in the boundary layer developed around the 50 mm diameter probe. The measured stagnation-point heat transfer rates are reported and discussed.

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