A two-dimensional parallel strand/CAMR solver for hypersonic flow simulations

Many Thermal Protection Systems (TPS) for hypersonic vehicles use ablating materials. In turn, this causes the vehicles' external geometry to change during flight. In this work a strand/Cartesian Adaptive Mesh Refinement solver has been used to simulate the hypersonic flow over recessing surfaces. This technique uses separate near-body and off-body domains that are joined by overset algorithms in order to create a highly-automated system. Results obtained using the new solver are presented including comparisons with single-domain and experimental results, along with a simulation including a recessing surface