| Issue |
Volume 3, 2012
Progress in Flight Physics
|
|
|---|---|---|
| Page(s) | 365 - 380 | |
| Section | Chapter Four. Heat Transfer | |
| DOI | https://doi.org/10.1051/eucass/201203365 | |
| Published online | 29 January 2013 | |
The methology for determination of catalytic properties of SiC samples for specified Pre-X and MSRO conditions
1
Institute of Mechanics M. V. Lomonosov Moscow State University Michurinskii Prosp. 1, Moscow 119192, Russia
2
Institute for Problems in Mechanics Russian Academy of Sciences Prosp. Vernadskogo 101/1, Moscow 119526, Russia
3
ONERA DMAE/C2A Av. E. Belin 2, Toulouse 31055, France
Numerical simulation of subsonic inductively coupled plasma (ICP) flow and exhausted air and CO2-plasma jets around of the flat-face model with SiC coating were performed for IPG-4 (IPM RAS) facility test regimes simulating of reentry heating of the Pre-X space vehicle (Earth) and the MSRO − Mars Sample Return Orbiter (MSRO) (Mars). The calculation of the body heat flux maps was based on numerical solution of one-dimensional equations of laminar thermally and chemically nonequilibrium multicomponent boundary layer with finite thickness. The necessary flow data at the outer edge of the boundary layer were taken from results of Navier-Stokes calculations. The result obtained in the framework of macroscopic approach shows that the SiC samples are a low catalytic material in regards with the specified operating conditions for the Pre-X and for the MSRO.
© Owned by the authors, published by EDP Sciences, 2012