Modeling of Heat Transfer Attenuation by Ablative Gases During the Stardust Reentry
Modeling of Heat Transfer Attenuation by Ablative Gases During the Stardust Reentry
- New search for: Martin, Alexandre
- New search for: Boyd, Iain D.
- New search for: Martin, Alexandre
- New search for: Boyd, Iain D.
Modern space vehicles designed for planetary exploration use ablative materials to protect the payload against the high heating environment experienced during reentry. To properly model and predict the aerothermal environment of the vehicle, it is imperative to account for the gases produced by ablation processes. The present study aims to examine the effects of the blowing of ablation gas in the outer flow field. Using six points on the Stardust entry trajectory at the beginning of the continuum regime, from 81 to 69 km, the various components of the heat flux are compared to air-only solutions. Although an additional component of the heat flux is introduced by mass diffusion, this additional term is mainly balanced by the fact that the translational–rotational component of the heat flux, the main contributor, is greatly reduced. Although a displacement of the shock is observed, it is believed that the most prominent effects are caused by a modification of the chemical composition of the boundary layer, which reduces the gas-phase thermal conductivity.
Document information
Modeling of Heat Transfer Attenuation by Ablative Gases During the Stardust Reentry
Journal of Thermophysics and Heat Transfer ; 29 , 3 ; 450-466
2015-04-08
17 pages
Article (Journal)
Electronic Resource
English
Similar titles
Modeling of Heat Transfer Attenuation by Ablative Gases During the Stardust Re-entry
| British Library Conference Proceedings | 2012
FULL-LENGTH PAPERS - Simulating Stardust Earth Reentry with Radiation Heat Transfer
| Online Contents | 2011
Modeling of Stardust Reentry Reacting Thermal and Chemical Ablation Flow
| British Library Conference Proceedings | 2007