Numerical simulation of nonequilibrium condensation in a hypersonic wind tunnel

A computational method for calculating supersonic two-dimensional nozzle flows with nonequilibrium phase change is developed. The code uses a fully implicit, finite volume formulation with Steger-Warming flux vector splitting and Jacobi point relaxation. Source terms for finite rate condensation and evaporation are constructed from the classical theories of nucleation and droplet growth. Calculations of the NASA Langley Research Center 8-ft High Temperature Tunnel nozzle are performed and compared with previously reported quasi-one-dimensional calculations and experimental data.