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.
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