Author ORCID Identifier

Date Available


Year of Publication


Degree Name

Doctor of Philosophy (PhD)

Document Type

Doctoral Dissertation




Mechanical Engineering

First Advisor

Dr. Alexandre Martin


Atmospheric entry occurs at very high speeds which produces high temperature around the vehicle. Entry vehicles are thus equipped with Thermal Protection Systems which are usually made of ablative materials. This dissertation presents a new solver that models the atmospheric entry environment and the thermal protection systems. In this approach, both the external flow and the porous heat shield are solved using the same computational domain. The new solver uses the Volume Averaged Navier-Stokes Equations adapted for hypersonic non-equilibrium flow, and is thus valid for both domains. The code is verified using analytical problems, set of benchmarks and also a code-to-code comparison is carried out. A validation study is conducted by modelling a hypersonic arc jet facility test case including ablation modelling. Finally, a high temperature flow tube experiment case is modelled for validation purposes and to study the ablation chemistry model.

Digital Object Identifier (DOI)

Funding Information

Financial support for this work was provided by The National Aeronautics and Space Administration Space Technology Research, Development, Demonstration, and Infusion 201x (NASA SpaceTech-REDDI) Award NNX16AD18G and Air Force Office of Scientific Research 2020 (AFOSR) FA9550-18-1-0261.