Variable Turbulent Prandtl Number Model for Shock/Boundary-Layer Interaction
Author:
Affiliation:
1. Indian Institute of Technology Bombay, Mumbai 400 076, India
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.J056183
Reference35 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
4. Computational Analysis of Shock Wave Turbulent Boundary Layer Interaction
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