Turbo & Agile

Best-in-class turbomachinery design tools from preliminary and detailed design to full 3D steady and unsteady CFD


Engineers looking to combine speed and accuracy for their virtual turbomachinery designs trust NUMECA, even for their toughest challenges.

We have designed a unique toolset that encompasses a complete end-to-end solution: 1D to 3D, Meshing, CFD and Optimization, all in one single environment. Thanks to more than 75 years of expertise in rotating machinery, the environment displays an unsurpassed ease-of-use and accuracy.

     Partner of NUMECA International

The strong partnership between NUMECA International, with its Flow Integrated Numerical Environment, and CONCEPTS NREC with its Agile Engineering Design System, gave rise to the fastest and most accurate CFD suite for Turbomachinery design on the market today.

The solution is up to 20x faster than the competition, allowing engineers to run multiple design points and geometry variations to ensure maximum product performance. 

Components range from multi-stage axial to radial to mixed-flow configurations (compressors, turbines, pumps, fans, propellers or contra-rotating propellers).

Our solutions can take into account uncertainties in operating conditions as well as manufacturing uncertainties, so engineers can simulate under real-world conditions and further enhance the reliability of their CFD results.


Non Linear Harmonics

Conjugate Heat Transfer



OMNIS™ - Power to explore, collaborate and innovate

One single integrated multiphysics environment for all steps in the simulation process, powered by the fastest solvers on the market.

Accurately predict real-world product performance through multiphysics simulation. Run all of your simulations in one place and change from one physics to another by the simple click of a button. 

Steer product design from start to finish through a highly automated and streamlined workflow.

Fidelity-to-Need - Built for the simplest to the most advanced simulation needs.



Case Studies

Key Features

Meanline design

For all major turbomachinery configurations. Meanline options include: 

  • COMPAL® for radial and mixed-flow compressors
  • PUMPAL® for radial, mixed-flow, axial pumps
  • RITAL™ for radial and mixed-flow turbines
  • AXIAL™ for axial compressors and turbines


Parallel Mesh Generation

  • Wizard mode: optimal mesh topology based on configuration
  • Advanced geometry features: blade fillets, cooling systems, axisymmetric and non-axisymmetric effects
  • Advanced configurations: multistage, bulb, unshrouded and by-pass
  • Automated blocking and meshing of axisymmetric effects
  • Python scripting technology


  • Multi-projects and multi-views graphical user interface
  • Specific turbomachinery visualization mode
  • Python scripting technology

FINE™/Open flow solver

  • One single code for all types of fluids (incompressible, low-compressible, condensable and fully compressible) and speed (low speed to hypersonic regime)
  • Acceleration with the CPU-Booster™ module provides 3-5 times gain in convergence speed
  • Embedded fluid structure interaction with the Modal and Flutter Analysis module
  • Multigrid convergence acceleration
  • Multidomain capability
  • Combustion
  • Radiation
  • Lagrangian multiphase
  • Cavitation
  • Multispecies reacting flows
  • Thermodynamics tables and combustion tables generation
  • Python scripting technology


  • OpenLabs™ allows users to customize or add physical models
  • Flexible and user-friendly Graphical User Interface
  • Users don’t need to care about programming details and code structure
  • OpenLabs can be used in a wide variety of industrial and academic applications
  • Identical computing and memory costs compared to source-coded models
  • Free access to all FINE™/Open community

FINE™/Turbo flow solver

  • One single code for all types of fluids (incompressible, perfect or real gas, compressible liquid and condensable) and speed (low speed to hypersonic regime)
  • Acceleration with the CPU Booster™ module provides 3-5 times gain in convergence speed
  • Non Linear Harmonic (NLH) module for full unsteady rotor-stator interactions with gains of 1 to 3 orders of magnitude in CPU time
  • Cross-out High Performance Computing (HPC) on supercomputers with linear speed-up on up to 5,000 to 10,000 cores
  • Embedded Fluid Structure Interaction (FSI) with the Modal and Flutter Analysis module
  • Uncertainty Quantification module to study the variability with respect to geometrical or operational uncertainties
  • Automated performance curve creation
  • Multigrid convergence acceleration
  • Full Non-Matching Boundaries capability
  • Laminar-turbulent transition
  • Congugate heat transfers
  • Cavitation
  • Python scripting technology

Detailed 3D design

For geometry and blading using AxCent®, including throughflow, 2D blade to blade and streamline curvature calculation.

  • 2D and radial blading
  • Agile links to COMPAL®, PUMPAL®, RITAL™,AXIAL™, FINE/Turbo, pbFEA and MAX-PAC
  • Bezier-based cross-section (axial) and geometry generation (radial)
  • Blade generation sheets
  • Blade lean
  • CAD output (IGES, STEP, ACIS, Parasolid, STL)
  • Circular-arc and line segment contours
  • Fillets (single-radious, variable, elliptical)
  • Ideal and real fluids
  • Independent hub and shroud
  • Multistreamtube (MST) calculation for both compressible and incompressible flow
  • Radial stacking of up to 3-cross-sections at LE, TE or CG
  • Rapid loading calculation for both compressible and incompressible flow
  • Single-blade raw capability
  • Suitable for compressors, fans, pumps and turbines
  • Swept leading and trailing edges
  • Throat area calculation
  • Add: BANIG
  • Add: Blade stacking of 2 to unlimited number of cross sections
  • Enhanced flank milling -  confirming ruled surface
  • Flow cuts and trims/extensions
  • Flow injection and extraction
  • Inlet boundary layer calculations
  • Non-axisymmetric walls
  • Parameterized blade types (MCA, DCA, Pritchard, Enhanced Pritchard)
  • Parameterized blade types (NACA, Constant Passage, simple airfoil)
  • Simple and independently-specified splitter blades (Independent was option)
  • Stacking curve adjustment in meridional and tangential directions



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