Density-Based Solver for the Simulation of High-Speed Air Flows over Aircrafts: rhoDST©
A density-based solver rhoDST© was developed for steady and unsteady simulations of high speed compressible flows over aeronautical vehicles. The rhoDST© solver has been developed based on foam-extend 4.1 libraries for the fully-coupled solution of governing equations on highly skewed unstructured meshes. This project was funded by Turkish Aerspace Industry.
Features
- Continuity, momentum and energy equations are implicity coupled in a block matrix. The corresponding matrix can be solved using block-matrix solvers such as GMRES, BiCGStab and multigrid methods.
- Local time stepping can be used for the fast convergence to the steady-state solution.
- Shock-discontinuities can be captured using Kurganov, AUSM, AUSM+, AUSM+up, HLL, HLLC and HLLCP shock-capturing methods.
- Modifications of SpalartAllamaras turbulence model were incorporated to the turbulence libraries. Simpler Rotation-Curvature and Spalart-Shur rotation/curvature correction are implemented to account for rotation and curvature effects. Negative Spalart-Allmaras was implemented to resolve numerical issues near the interface between turbulent and irrotational regions.
- Characteristic far-field boundary conditions were used at the outer boundaries for subsonic, transonic and supersonic freestream flows.
Examples
Various problems were simulated using the rhoDST© solver and validated for subsonic, transonic and supersonic flows.
Forward-facing step problem
Transient simulation of supersonic laminar flow over a forward facing step for Ma = 3
Transonic flow over RAE2822
Steady-state simulation of transonic turbulent flow over RAE2822 airfoil for Ma = 0.729
Transonic flow over ONERA M6
Steady-state simulation of transonic laminar flow over ONERA M6 Wing for Ma = 0.8395
Turbulent flow over a full-aircraft model
Steady-state simulation of transonic turbulent flow over a full-aircraft model for Ma = 0.9
