Assessment of turbulence and transition models for predicting surface heat flux in hypersonic flow | ||
| Journal of Engineering Science and Military Technologies | ||
| Articles in Press, Accepted Manuscript, Available Online from 01 October 2025 | ||
| Document Type: Original Article | ||
| DOI: 10.21608/ejmtc.2025.421247.1335 | ||
| Authors | ||
| ahmed m yassin* 1; Mahmoud Yehia2; Osama Mohamed kamal Mohamed mahmoud3 | ||
| 1Military technical college | ||
| 2MTC | ||
| 3Rockets drpartment, Aeronautics & Astronautics Branch, Military Technical College | ||
| Abstract | ||
| Hypersonic flight regime is uniquely characterized by severe aerodynamic phenomena that are dictated by surface thermal conditions. Predicting surface heat flux to hypersonic vehicles is gaining more focus as civilian applications of these vehicles increases. Commercial CFD solvers provide a variety of turbulence and transition models that are usable in predicting heat flux in hypersonic conditions. Accuracy of these models compared with experimental measurements remains an open question. This study contributes in assessing various turbulence and transition models available in a commercial CFD solver. Three turbulence models namely, the 1-equation Spalart–Allmaras, the 2-equation k–ω, and the 6-equation Reynolds Stress turbulence models are tested along with the γ and γ–Reθ transition models. Simulations are carried out on a thermal non-equilibrium real gas model with a multi-species mixture of air in order to simulate high-temperature effects. Simulations are compared on their ability to predict heat flux, with emphasis on model sensitivity and comparison to theoretical or experimental benchmarks. The outcomes enlighten the suitability and limitation of common models for high-fidelity aerothermal prediction in hypersonic flow applications. | ||
| Keywords | ||
| Boundary Layer; Heat Flux; Hypersonic flow; High-temperature effects; Non-equilibrium real gas | ||
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