We present a parallel solver for performing full-trajectory simulations of hypersonic ablating bodies and re-entry vehicles. The solver fully couples computational fluid dynamic simulation of the flowfield, including ablation products, and the solid response including shape changes. The formulation is based on the state-of-the-art ablation model for carbon ablators in air from the widely used CMA code. It uses an equilibrium gas formulation for the flowfield physics that is based on the NASA CEA thermodynamic database. Results are presented for two ablation calculations to demonstrate the computational capability of the code.