Abstract
Gas surface interaction phenomena behind the shock wave in front of space vehicles during the reentry phase can only be investigated in high-enthalpy facilities with a long testing time. Sintered silicon carbide and carbon fibre-reinforced silicon carbide samples have been tested at different test conditions in the LBK. Experimental results concerning the gas parameters have been supported by numerical computation including chemical non-equilibrium processes in the nozzle flow coupled with frozen or equilibrium shock solutions. Spectroscopic analyses of the material composition of the samples tested in the air atmosphere indicate the development of a protective SiO2-layer.
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© 1995 Springer-Verlag Berlin Heidelberg
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Gülhan, A. (1995). Interaction of Thermal Protection Materials with the High-Enthalpy Flow of the Arc-Heated Wind Tunnel LBK. In: Brun, R., Dumitrescu, L.Z. (eds) Shock Waves @ Marseille I. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-78829-1_17
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DOI: https://doi.org/10.1007/978-3-642-78829-1_17
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-78831-4
Online ISBN: 978-3-642-78829-1
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