Non-equilibrium effects on hypersonic flow over a reentry vehicle are studied using
numerical simulations. A parallel, finite-volume based flow solver is developed using
a modified Steger-Warming flux vector splitting scheme. Vibrational, chemical and
thermal non-equilibrium effects are accounted for. Several physical models with increasing
levels of physical complexity are included. The flow solver is validated using
standard problems like vortex convection, periodic shock-tube and shock/vortex interaction.
The hypersonic flow over a cylinder is performed and a surface profile for pressure
is obtained. For non-equilibrium effects, a perfectly stirred reactor with 5 species
is simulated to account for vibrational and chemical non-equilibrium effects. Future
simulations are to be assessed over a wide range of Mach numbers. Convective and
radiative heat transfer rates over the surface are to be investigated.