Abstract
Aerothermodynamics analysis of the Orion crew exploration vehicle (CEV) reentry vehicle at high altitude has been studied numerically. At high altitude in the rarefied flow regime noncontinuum technique such as direct simulation Monte Carlo (DSMC) method is used to solve the Boltzmann equation of kinetic theory. Results are reported at different altitudes in the rarefied regime for ideal gas and real gas model. The effects of nose radius and free stream velocity are presented. The estimation of bow shock strength and peak surface heat flux is higher for ideal gas compared with real gas model. The flow field characteristics have shown significant change with decrease in altitude and increase in free stream velocity. Present results are matching well with the results available in the literature.
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