Numerical Simulation Of Supersonic Compression Ramp Flow
| Autor: | Ki-Hyuk Yang et.al |
|---|---|
| Rok vydání: | 2021 |
| Předmět: |
Shock wave
Turbulence Adaptive mesh refinement business.industry Computer science General Mathematics Mechanics Computational fluid dynamics Education Physics::Fluid Dynamics Computational Mathematics symbols.namesake Flow separation Computational Theory and Mathematics Mach number symbols Supersonic speed business Transonic |
| Zdroj: | Turkish Journal of Computer and Mathematics Education (TURCOMAT). 12:812-821 |
| ISSN: | 1309-4653 |
| Popis: | Shock wave/boundary layer interaction (SWBLI) is a highly critical problem that occurs in aircraft in transonic or supersonic flow. This study performed CFD analysis of the supersonic ramp flow of freestream Mach number 2.79. To secure reliability of the CFD analysis, adaptive mesh refinement using a gradient p sensor was used. Through this, a grid of sufficient resolution was obtained for the region of shock wave, expansion wave, and flow separation. The prediction performance of 7 turbulence models that are widely used in engineering application were compared. The baseline k–ω two-equation model showed the best prediction performance, while the SST k–ω model, which is one of the most widely used two-equation models, and the 2 Reynolds stress models showed relatively poor prediction performance. In the SWBLI problem, the use of adaptive mesh refinement made it possible to secure sufficient grid resolution; meanwhile, comparison of the prediction performance of the various turbulence models confirmed that for the SWBLI problem, the generally used turbulence model was somewhat inappropriate. |
| Databáze: | OpenAIRE |
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