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The Inflatable Reentry and Descent Technology flight performed in 2006 was not nominal. The flight was characterized by a blackout period shorter than expected. Here, we apply two methods that can be used to perform postflight analysis. The first, based on an engineering approach, has already been used for the preflight analysis. The second involves coupled calculations between a computational fluid dynamics and an electromagnetic solver. The main objective of this postflight analysis is to validate this advanced approach using flight data and to assess the validity of the engineering method. Numerical results show that the engineering method overpredicts the blackout duration due to the fact that this method is based on a severe on/off switch. The coupled approach leads to an underestimation of the blackout period. Several uncertainties, such as the influence of ablative material on ionization, could explain this discrepancy. Analysis establishes the validity of the coupled approach, but its accuracy depends strongly on the modeling used for the calculations.Nomenclature E z = Z component of the electric field in the direction of Earth, V=m F np = Fourier transform without plasma F p = Fourier transform in the presence of plasma f link = link frequency, Hz f p = plasma frequency, Hz m e = electron mass, kg n e = electron number density, m 3 n e;crit = critical electron number density, m 3 q = electron charge, C t = time from launch, s " 0 = permittivity of vacuum, F=m

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In the frame of future sample return missions to Mars, asteroids, and comets, investigated by the European Space Agency, a review of the actual aerodynamics and aerothermodynamics capabilities in Europe for Mars entry of large vehicles and high-speed Earth reentry of sample return capsule has been undertaken. Additionally, capabilities in Canada and Australia for the assessment of dynamic stability, as well as major facilities for hypersonic flows available in ISC, have been included. This paper provides an overview of European current capabilities for aerothermodynamics and testing of thermal protection systems. This assessment has allowed the identification of the needs in new facilities or upgrade of existing ground tests for covering experimentally Mars entries and Earth high-speed reentries as far as aerodynamics, aerothermodynamics, and thermal protection system testing are concerned.

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