PlasFlowSolver: An Aero thermo dynamic Data Reduction Model for Inductively Coupled Plasma Wind Tunnel Facilities

Aero thermodynamic data reduction models are useful tools for analyzing experiments in high-enthalpy plasma wind tunnels, which are essential for evaluating materials used in hypersonic and reentry applications. This study introduces Plas Flow Solver, a data reduction model developed to estimate flow properties such as temperature, enthalpy, and velocity from experimental data, including pressure, stagnation pressure, and stagnation-point cold-wall heat flux. The model is based on boundary layer theory and assumes thermochemical equilibrium, providing an engineering framework for efficient analysis. The model assumptions and the computation of the stagnation-point cold-wall heat flux are thoroughly discussed. Sensitivity analyses of input parameters, such as wall temperature and jet radius, explore the applicability of the model. Results are presented, including the generation of a high-altitude partial operational map for the Plasmatron X wind tunnel at the University of Illinois at Urbana-Champaign. Limitations are discussed, and verification against an existing model is provided.