The present paper presents the in-flight measurement of the transpiration cooling experiment AKTiV flown on the sub-orbital re-entry configuration SHEFEX II. Heat flux to the structure is measured just up- and downstream of the cooled sample. The measurement shows that heat flux is reduced upon coolant exhaust. Uncooled temperatures measured on the reference set-up are on the order of 380 K. The maximum temperature reduction by transpiration-cooling is observed on the porous sample with 87 K, while downstream the sample, there is still a temperature reduction by 75 K by film cooling. The evaluation is supported semi-analytical tool HEATS, based on a transient heat balance at the surface. The analysis shows that the flow condition remains longer laminar than expected. Comparison of the results with HEATS shows that the heat flux predicted with HEATS is in good concurrence with the measured temperatures on the cooled sample, as well as upstream and downstream with a maximum deviation by 14%.
Transpiration Cooling at Hypersonic Flight AKTiV on SHEFEXII
2014
12 Seiten, Bilder, 21 Quellen
Conference paper
English
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