Summary
Two active cooling concepts were tested concerning their capabilities with respect to surface cooling in hypersonic flow. Film cooling was analysed in cold hypersonic flow at realistic Reynolds numbers. Cooling efficiency was found highly sensitive to injection geometry and flow inclination. Best performance was observed for helium with a heat flux reduction up to 90% compared to the non-cooled case. Transpiration cooling was thermally qualified in high enthalpy flow. The coolant was supplied through a porous material integrated in the surface. Substantial cooling could be achieved in the injection area and further downstream at low coolant flow rates. Optimal flow rates could be identified for several coolants.
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References
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Esser, B., Gülhan, A. (2008). Qualification of Active Cooling Concepts in Ground Facilities. In: Gülhan, A. (eds) RESPACE – Key Technologies for Reusable Space Systems. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 98. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-77819-6_7
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DOI: https://doi.org/10.1007/978-3-540-77819-6_7
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