A parallel implicit CFD code for the simulation of ablating re-entry vehicles

Research output: Chapter in Book/Report/Conference proceedingConference contribution

11 Scopus citations

Abstract

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.

Original languageEnglish (US)
Title of host publication47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
StatePublished - Dec 1 2009
Event47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition - Orlando, FL, United States
Duration: Jan 5 2009Jan 8 2009

Publication series

Name47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition

Other

Other47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
CountryUnited States
CityOrlando, FL
Period1/5/091/8/09

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    Nompelis, I., Candler, G. V., & Conti, R. J. (2009). A parallel implicit CFD code for the simulation of ablating re-entry vehicles. In 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition [2009-1562] (47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition).