Three-dimensional thermochemical nonequilibrium flow modeling for hypersonic flowsA three-dimensional thermochemical nonequilibrium model has been developed and applied to the study of entry flows surrounding space vehicles. The model accounts for both chemical and vibrational nonequilibrium phenomena behind the bow shock. The thermodynamic state of a real gas is modeled with a translational-rotational temperature and a electron-vibrational temperature. Their internal energies are averaged to determine the temperature used in the reaction rates calculation. In order to establish the validity of the selected models, both one- and two-temperature models with seven and/or eleven species were investigated. Several numerical experiments that include a sphere, the RAMC vehicle and 3D AFE forebody flows were performed. Preliminary results were compared with RAMC-II experimental data. Good agreement was obtained after a two-temperature model with eleven species and thirty reactions was incorporated into the study.
Document ID
19890054716
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Tam, L. T. (Lockheed Engineering and Sciences Co. Houston, TX, United States)
Li, C. P. (NASA Johnson Space Center Houston, TX, United States)