sonicDyMFoam - OpenFOAM Solver

Solver: sonicDyMFoam   Description

sonicDyMFoam is a pressure-based solver designed for transient simulations of compressible flow. It handles laminar and turbulent, single-phase flows with temperature and density variations (it solves the energy equation). It is an extension of the sonicFoam solver additionally supporting the functionality of dynamic mesh motion.

The solver uses the PIMPLE (merged PISO-SIMPLE) algorithm for pressure-momentum coupling. This algorithm leverages the strengths of both PISO and SIMPLE methods for pressure-velocity coupling, ensuring robustness in handling transient flows with large time steps. This approach is supplemented by under-relaxation techniques to secure convergence stability. It supports both Multiple Reference Frame (MRF) and porosity modeling and allows easy integration of passive scalar transport equations and source terms.

The dynamic mesh capabilities of this solver expand its scope for analyzing moving objects. In the aerospace aerodynamics it can simulate the effect of moving control surface (e.g. flaps) on the aircraft’s performance. The solver can simulate the turbine blade fluttering in the turbomachinery industry. For the rocket exhaust systems, it can be used to analyze the changing geometry of the nozzle.

Solver: sonicDyMFoam   Features

  • Transient
  • Compressible
  • Single-Phase
  • High-Speed Aerodynamics
  • Transonic Flow
  • Supersonic Flows
  • Pressure-Based Solver
  • Shock Waves Capturing
  • Dynamic Mesh Motion
  • Laminar and Turbulent (RANS, LES, DES)
  • Equation of State Models
  • Rotating Objects:
    • Multiple Reference Frames (MRF)
    • Rotating Mesh Motion
  • Passive Scalar
  • Porosity Modeling
  • Heat Transfer
  • Heat Source (energy source therm)
  • Source Term (explicit/implicit)
  • PIMPLE Algorithm
  • Solution Limiters:
    • Velocity Damping
    • Temperature Limit

Solver: sonicDyMFoam   Application

Aerospace Industry

  • Flight Control Systems Movement and Aircraft Performance

Wind Tunnel Simulations

  • Moving Objects in the Wind Tunnel

Exhaust Systems

  • Changing Geometry of the Nozzle

Solver: sonicDyMFoam   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 and high-speed aerodynamics (Ma > 0.3)

Subsonic / Transonic, Steady-State, Ma < 1

Subsonic / Transonic, Transient, Ma < 1

Transonic / Supersonic, Pressure-Based, Ma > 1

Transonic / Supersonic, Density-Based, Ma > 1

  • Ma - Mach Number
  • DyM - Dynamic Mesh
  • Overset - also known as Chimera Grid (Method)

Solver: sonicDyMFoam   Results Fields

This solver provides the following results fields:

  • Primary Results Fields - quantities produced by the solver as default outputs
  • Derivative Results - quantities that can be computed based on primary results and supplementary models. They are not initially produced by the solver as default outputs.

Primary Results Fields


\(U\) [\(\frac{m}{s}\)]


\(T\) [\(K\)]


\(p\) [\(Pa\)]

Derivative Results


\(\rho\) [\(\frac{kg}{m^{3}}\)]


\(\omega\) [\(\frac{1}{s}\)]

Mach Number

\(Ma\) [\(-\)]

Courant Number

\(Co\) [\(-\)]

Peclet Number

\(Pe\) [\(-\)]

Stream Function

\(\psi\) [\(\frac{m^2}{s}\)]

Q Criterion

\(Q\) [\(-\)]

Wall Functions (for RANS/LES turbulence)

\(y^+\) [\(-\)]

Wall Shear Stress

\(WSS\) [\(Pa\)]

Wall Heat Flux

\(\phi_q\) [\(W/m^2\)]

Turbulent Fields (for RANS/LES turbulence)

\(k\) \(\epsilon\) \(\omega\) \(R\) \(L\) \(I\) \(\nu_t\) \(\alpha_t\)

Volumetric Stream

\(\phi\) [\(\frac{m^{3}}{s}\)]

Passive Scalar

\(scalar_i\) [\(-\)]

Forces and Torque acting on the Boundary

\(F\) [\(N\)] \(M\) [\(-\)]

Force Coefficients

\(C_l\) [\(-\)] \(C_d\) [\(-\)] \(C_m\) [\(-\)]

Average, Minimum or Maximum in Volume from any Result Field

\(Avg\) \(Min\) \(Max\)