Summary
In this study fundamental investigations concerning film cooling on an inclined flat plate and on a stagnation point region in laminar flow are performed. The influence of the relevant parameters, i.e. the Reynolds number of the free stream, the blowing ratio and the geometry of the blowing opening, is investigated by experiments. The results show the weak influence of the cooling gas injection on the outer flow. But the experimental data achieved in a shock tunnel demonstrate that already low blowing rates lead to a significant reduction of the thermal loads. Overall the results exhibit that the film cooling technique is an effective method for cooling bodies in laminar hypersonic flows.
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Heufer, K.A., Olivier, H. (2008). Experimental Study of Active Cooling in 8 Laminar Hypersonic Flows. 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_8
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DOI: https://doi.org/10.1007/978-3-540-77819-6_8
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