Evaluation of the SU2 Open-Source Code for a Hypersonic Flow at Mach Number 5

This paper presents the evaluation of Stanford University Unstructured (SU2) open-source computational software package for a high Mach number 5 flow. The test case selected is an impinging shock wave turbulent boundary layer interaction (SWTBLI) on flat plate where experimental data Sch¨ulein et al. [27] used validation purposes. Two turbulence models, Spalart–Allmaras (SA) and k-ω Shear Stress Transport (SST) within SU2 code are evaluated in this study. Flow parameters, such as skin friction, wall pressure distribution profiles compared with values. results demonstrate performance at flow highlight its limitations predicting fluid physics. At higher generator angles, discrepancy between CFD more significant. Within separation zones, smaller bubble delayed predicted by SA model while SST predicts early separation. Both models able to predict correctly However, discrepancies were observed prediction friction due inability capture recovery after impingement.