Solver: rhoCentralFoam Description
rhoCentralFoam is a density-based solver designed for transient simulations of compressible flow. It handles laminar and turbulent, suitable for high-speed aerodynamic applications.
The core of the solver is the central-upwind schemes for convective fluxes. This method is well-regarded for its balance between accuracy and robustness in capturing shock waves and other steep gradient phenomena inherent in compressible flows. This approach ensures reliable and precise simulations, particularly in scenarios involving complex shock interactions and rapid changes in flow properties. It supports Multiple Reference Frame (MRF), porosity modeling and allows easy integration of passive scalar transport equations and source terms. The solver handles dynamic meshes.
The solver is used in industries where the dynamics of compressible flows are critical. This includes the aerospace sector for the analysis and design of high-speed aircraft, the automotive industry for studying the effects of airflow over high-speed vehicles, and the energy sector for the design and optimization of turbines and compressors. In the military industry, it can be used for high-speed bullets and missile analysis.
Solver: rhoCentralFoam Features
- Transonic Flow
- Supersonic Flows
- Density-Based Solver
- Shock Waves Capturing
- Laminar and Turbulent (RANS, LES, DES)
- Equation of State Models
- Passive Scalar
- Heat Transfer
- Central Differencing Scheme
- Solution Limiters:
- Velocity Damping
- Temperature Limit
Solver: rhoCentralFoam Application
- High-speed Aircraft Aerodynamics
- High-speed Airplanes Wing Profiles
- Rockets Entry to the Atmosphere
- Bullets and Missiles
- Converging-diverging Nozzles in Engines
Solver: rhoCentralFoam Compressible Solvers Comparison
Compressible Solvers In this group, we have included single-phase, pressure and density-based solvers that can handle flows with significant variations in density, mostly applicable for low and high-speed aerodynamics (Ma > 0.3)
Subsonic / Transonic, Ma < 1
Transonic / Supersonic, Ma > 1
- Ma - Mach Number
- DyM - Dynamic Mesh
- Overset - also known as Chimera Grid (Method)
Solver: rhoCentralFoam Tutorial
- A 2D analysis of supersonic flow through the tunnel with inclined wedge using a density-based solver (Rho Central) visualizes the resulting shock wave.