Variable turbulent Prandtl number model applied to hypersonic shock/boundary-layer interactions
Author:
Affiliation:
1. Indian Institute of Technology Bombay
Publisher
American Institute of Aeronautics and Astronautics
Link
https://arc.aiaa.org/doi/pdf/10.2514/6.2018-3728
Reference39 articles.
1. Progress in shock wave/boundary layer interactions
2. Hypersonic Shock Wave Impingement on Turbulent Boundary Layers: Computational Analysis and Uncertainty
3. Review and assessment of turbulence models for hypersonic flows
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