Multi-dimensional modeling of charring ablators

Haoyue Weng, Huaibao Zhang, Ovais U. Khan, Alexandre Martin

Research output: Contribution to conferencePaperpeer-review

6 Scopus citations


Re-entry of a spacecraft occurs at the hypersonic regime where the flow field is extremely complex: high temperature gradients occurring in the shock-layer region ionize and dissociate the air. Even if a large portion of heat generated during this process is convected away in the surrounding air, a fraction of it is still transferred to the vehicle. Therefore, it is important to protect the vehicle with a suitable kind of shielding. Of the many techniques available today, use of ablative material is gaining popularity. The basic idea behind an ablating heat shield is that the energy incident on the spacecraft is used to vaporized the material, thus preventing a significant part of the heat to be transferred into the structure. The available literature indicates that most of the past investigations either do not consider the actual physical processes taking place during ablation, or are limited to a one-dimensional model. The present investigation shows the development of a numerical model for simulating the multi-dimensional heat transfer phenomena that occurred in a typical ablative TPS. The newly developed model is verified using closed form analytical solutions and validated with available data. This effort consists of the first steps of an ongoing project to develop a comprehensive multi-scale, multi-physics and multi-dimensional material response code aimed at modeling charring and surface ablators.

Original languageEnglish
StatePublished - Jun 25 2012
Event43rd AIAA Thermophysics Conference 2012 - New Orleans, LA, United States
Duration: Jun 25 2012Jun 28 2012


Conference43rd AIAA Thermophysics Conference 2012
Country/TerritoryUnited States
CityNew Orleans, LA

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering
  • Condensed Matter Physics


Dive into the research topics of 'Multi-dimensional modeling of charring ablators'. Together they form a unique fingerprint.

Cite this