High-Fidelity CFD Simulation of Supersonic Flow Over a Forward-Facing Step
Document Type
Conference Proceeding
Publication Date
7-29-2024
Abstract
A forward-facing step was analyzed in supersonic flow at a free-stream Mach number of 1.5 using structured, overset CFD methods with a hybrid RANS/LES turbulence model to assess shock-boundary layer interaction effects. Grid refinement was analyzed using automated multigrid cycling, and results indicate further grid refinement may be warranted. General flow features, boundary layer separation location, and shock unsteadiness match those found in the literature. A correlation study was conducted, and it was determined that the spanwise dimension of the grid system is appropriately sized for periodic boundary conditions.
Source Publication
AIAA AVIATION FORUM AND ASCEND 2024
Recommended Citation
Sirak, E., Sherer, S. E., Crowe, D. S., & Smith, M. J. (2024). High-Fidelity CFD Simulation of Supersonic Flow Over a Forward-Facing Step. AIAA AVIATION FORUM AND ASCEND 2024, Session: Supersonic/Hypersonic Applications II, AIAA 2024-3836. https://doi.org/10.2514/6.2024-3836
Comments
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