Abstract
It is hypothesized that spallation could affect the aerodynamic heating rates of reentry vehicles using ablative heat shields. To investigate spallation effects, a code is developed to compute the dynamics of spalled particles. The code uses a finite-rate chemistry model to study the chemical interactions of the particles with the flow field. The spallation code is one-way coupled to a computational fluid dynamics solver that models the hypersonic flow field around an ablative sample. Spalled particle behavior is numerically studied in both argon and air flow fields.
Original language | English |
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Pages (from-to) | 32-41 |
Number of pages | 10 |
Journal | Journal of Thermophysics and Heat Transfer |
Volume | 30 |
Issue number | 1 |
DOIs | |
State | Published - 2016 |
ASJC Scopus subject areas
- Condensed Matter Physics
- Aerospace Engineering
- Mechanical Engineering
- Fluid Flow and Transfer Processes
- Space and Planetary Science