V. Carandente1, R. Savino1, M. Iacovazzo1, C. Boffa
FDMP-Fluid Dynamics & Materials Processing, Vol.9, No.4, pp. 461-484, 2013, DOI:10.3970/fdmp.2013.009.461
Abstract The article deals with the aerothermal analysis of a sample-return hypersonic capsule reentering on Earth from an interplanetary exploration mission. The main objective of the work is to estimate the heat flux distribution on the capsule surface and to perform one-dimensional thermal analyses for its ablative heat shield. After a short review of sample-return missions, the numerical models implemented are described and the computational results, obtained along a feasible reentry trajectory, are presented and discussed. Particular attention has been paid to compare the convective stagnation point heat fluxes obtained by means of Computational Fluid Dynamic More >
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