Application of HyperCODA to Hypersonic Flows Around Two-Dimensional Geometries

Abstract

This paper presents a detailed analysis of the HyperCODA flow solver's applicability in studying hypersonic phenomena relevant to both research and industrial contexts. The investigation focuses on exploring HyperCODA capabilities, validating its accuracy, and assessing computational requirements and efficiency in handling high enthalpy flows. Through comparative analysis with the DLR CFD solver TAU, we conducted a detailed study on two specific test cases: a two-dimensional 7/40 degree cone-flare at Mach 5.9 and a free shear layer generated by parallel flows separated by a viscous wall. In particular, the code-to-code comparison is performed between the solutions using an implicit time integration of RANS turbulence modeling, finite volume numerical method, and a single perfect gas. The analysis revealed generally good agreement besides minor discrepancies attributable to the different spatial discretization between the codes. This analysis highlights the potential for further enhancements in HyperCODA, particularly in stabilizing the two-equation turbulent model and addressing variations in flow separation and recirculation areas, thus advancing its utility in hypersonic research and industrial applications.