Simulation and Modeling of Hypersonic Turbulent Boundary Layers with Varied Reynolds Numbers and Pressure Gradients
Abstract
Hypersonic flight is currently a priority for the US Department of Defense, but technology development in this area is limited by the lack of sufficiently accurate design tools based on the Reynolds-Averaged Naiver Stokes (RANS) framework for the extreme drag andheating associated with high-speed, high Reynolds number turbulent flow in the boundary layer region. The objectives of the proposed work are to (1) perform direct numerical simulations (DNS) of hypersonic turbulent boundary layers with varied Reynolds numbers and pressure gradients for canonical yet Navy relevant flow configurations, and (2) subsequently use the DNS database to characterize boundary-layer physics and evaluate detailed turbulence statistics and flow features that are relevant to both operator-aware and data-driven RANS turbulence models. The PI will work closely with the experimental groups at Texas A&M University and Stevens Institute of Technology to ensure that the unique strengths of experiments and high-fidelity simulations can be exploited in a synergistic fashion for turbulence model development. The research team will also collaborate with turbulence modeling experts to assess the limitations of the currently available turbulence models and explore machine-learning techniques to augment and correct the existing models.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Mar 03, 2023
- Source ID
- N000142312304
Entities
People
- Lian Duan
Organizations
- Office of Naval Research
- Ohio State University
- United States Navy