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Tutorials
Tutorials show you how to use Simcenter STAR-CCM+ for various applications in a step-by-step format with recommendations for setup, initialization and steps of the solution process specific to the application. Macro and simulation files are available for download for a large proportion of cases.
Compressible Flow
The tutorials in this set illustrate various Simcenter STAR-CCM+ features for compressible fluid flows as well as harmonic balance.
Anisotropic Volume Meshing: Onera M6 Wing
When meshing aerospace geometries such as wings, propeller blades, or turbine blades, you are required to generate a very fine mesh that adequately captures the curvature of the leading and trailing edges. To help reduce the cell count while maintaining solution accuracy, Simcenter STAR-CCM+ provides an anisotropic meshing option by which you can refine these edges.
Setting Initial Conditions
Setting appropriate initial conditions is important as they influence how long the solver takes to reach convergence. Here, you specify a velocity that matches the overall Mach number of the flow.

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Tutorials
Tutorials show you how to use Simcenter STAR-CCM+ for various applications in a step-by-step format with recommendations for setup, initialization and steps of the solution process specific to the application. Macro and simulation files are available for download for a large proportion of cases.
- Using Tutorial Macros and Files
  Macros, input files, and final simulation files for a range of tutorials are provided as an optional download package on the Support Center website. These macros and final simulation files are provided as an aid to the written tutorials, so that you can check your final results against the downloaded files, or against a simulation that is built and run using the macros.
- Introduction
  Welcome to the Simcenter STAR-CCM+ introductory tutorial. In this tutorial, you explore the important concepts and workflow. Complete this tutorial before attempting any others.
- Foundation Tutorials
  The foundation tutorials showcase the major features of Simcenter STAR-CCM+ in a series of short tutorials.
- Geometry
  The tutorials in this set illustrate various Simcenter STAR-CCM+ features for creating and working with parts and 3D-CAD.
- Mesh
  The tutorials in this set illustrate various STAR-CCM+ features for building CFD meshes.
- Incompressible Flow
  The tutorials in this set illustrate various Simcenter STAR-CCM+ features for incompressible fluid flows as well as porosity and solution recording
- Compressible Flow
  The tutorials in this set illustrate various Simcenter STAR-CCM+ features for compressible fluid flows as well as harmonic balance.
  - Subsonic Flow: NACA-Type Intake
    This tutorial illustrates how to solve a three-dimensional compressible flow problem using Simcenter STAR-CCM+.
  - Transonic Flow: RAE2822 Airfoil
    The tutorial simulates two-dimensional, turbulent, compressible, transonic air flow over an idealized airfoil.
  - Transonic Flow: RAE2822 Airfoil Using Overset Mesh
    This tutorial demonstrates how to use an overset mesh to simulate transonic flow over the RAE2822 airfoil.
  - Anisotropic Volume Meshing: Onera M6 Wing
    When meshing aerospace geometries such as wings, propeller blades, or turbine blades, you are required to generate a very fine mesh that adequately captures the curvature of the leading and trailing edges. To help reduce the cell count while maintaining solution accuracy, Simcenter STAR-CCM+ provides an anisotropic meshing option by which you can refine these edges.
    - Loading the Simulation
      You start this tutorial by loading a simulation file that contains the Onera M6 wing.
    - Creating a Spherical Far-Field Boundary
      In this tutorial, you create a sphere where the outer surface represents the far-field conditions of the flow.
    - Creating the Fluid Region
      To use the Onera M6 wing in a simulation, you first convert the model to a geometry part, and then assign the part to a region. After creating the region, the outer boundary is set to a free-stream boundary which allows you to model free-stream conditions in the far-field.
    - Preparing and Generating the Mesh
      After assigning parts to regions and setting the boundary types, you can define the mesh settings for the volume mesh. For this simulation, you generate an anisotropic and aligned volume mesh based on an initial quadrilateral surface mesh.
    - Selecting the Physics Models
      Physics models define the physical variables and phenomena in the simulation. In this tutorial, the air is described by the ideal gas law and turbulence is accounted for by the Spalart-Allmaras turbulence model.
    - Setting Material Properties
      Set the material properties for air.
    - Setting Boundary Conditions
      The boundary conditions for the farfield are specified so as to account for the angle of attack with which the wing faces the oncoming flow.
    - Setting Initial Conditions
      Setting appropriate initial conditions is important as they influence how long the solver takes to reach convergence. Here, you specify a velocity that matches the overall Mach number of the flow.
    - Preparing Scenes for Shock and Mach Number
      For visualization, you create two scalar scenes: a pressure coefficient scene to visualise the lambda shock on the wing and a Mach number scene.
    - Plotting Simulation and Experimental Data
      Plot the lift and drag coefficients to determine when the analysis has reached convergence. The pressure coefficient on the wing is then compared against the experimental data [reflink]. In order to compare simulation results with experimental results, you create a normalized coordinate for a section of the wing.
    - Running the Simulation
      Before running the simulation, you define the solver settings and stopping criteria. You are advised to run this tutorial on a multi-core machine with four cores or more.
    - Visualizing the Results
      After the solution finishes, you can view the results of the simulation.
    - Validating the Results
      Compare the numerical results against experimental data.
    - Bibliography
  - Adaptive Mesh Refinement: Hypersonic Flow
    Hypersonic flows and flight envelopes present unique challenges in Computational Flow Dynamics. The extreme gradients and shocks can push flow solvers to their limits and resolving the flow features, particularly shock formation, is of paramount importance in obtaining valid converged solutions. In Simcenter STAR-CCM+, you can apply Adaptive Mesh Refinement (AMR) to accurately resolve developing shocks using refinement based on solution gradients.
  - Harmonic Balance: Single Stage Periodic Flow
    The tutorial illustrates the steps necessary to simulate a single axial compressor blade row so that the effect of a periodic wake can be analyzed using the Harmonic Balance method.
  - Gas Turbine Aerodynamics: Post-Processing
    In turbomachinery studies, the analysis of the flow field throughout the blade passage requires advanced post processing methods.
- Heat Transfer and Radiation
  The tutorials in this set illustrate various Simcenter STAR-CCM+ features for heat transfer, radiation, and thermal comfort.
- Multiphase Flow
  The tutorials in this set illustrate various Simcenter STAR-CCM+ features for simulating multiphase fluid flow problems
- Discrete Element Method
  The tutorials in this set illustrate various Simcenter STAR-CCM+ features for simulating Discrete Element Method problems
- Motion
  The tutorials in this set illustrate various STAR-CCM+ features for simulating problems with moving geometries and meshes, dynamic fluid body interaction, and rigid body motion:
- Reacting Flow
  The tutorials in this set illustrate various Simcenter STAR-CCM+ features for simulating reacting flows such as combustion.
- Solid Stress
  The tutorials in this set illustrate various Simcenter STAR-CCM+ features for computing deformation, strain, and stresses in solid regions. They also show how such computations can be coupled to the fluid behavior in an analysis of fluid-structure interaction.
- Aeroacoustics
  The tutorials in this set illustrate various Simcenter STAR-CCM+ features for solving aeroacoustic simulations.
- Electromagnetism
  The following tutorials illustrate features for solving problems that involve electromagnetic fields.
- Electrochemistry
  The following tutorial demonstrates chemical reactions induced by an electrical current.
- Battery
  The tutorials in this set illustrate various Simcenter STAR-CCM+ features for setting up a battery model:
- Automation
  The tutorials in this set illustrate various Simcenter STAR-CCM+ automation and macro features.
- Design Exploration
  The tutorials in this set illustrate various features for running design exploration studies in Design Manager.
- Coupling with CAE Codes
  The tutorials in this set illustrate various Simcenter STAR-CCM+ features for coupling with CAE codes:
- Analysis Methods
  The tutorials in this set illustrate various Simcenter STAR-CCM+ features for analysing and visualizing simulation data.
- Simcenter STAR-CCM+ In-cylinder
  The tutorials in this set illustrate features for simulating internal combustion engines in Simcenter STAR-CCM+ using the dedicated add-on Simcenter STAR-CCM+ In-cylinder.

Setting Initial Conditions

Setting appropriate initial conditions is important as they influence how long the solver takes to reach convergence. Here, you specify a velocity that matches the overall Mach number of the flow.

The initial velocity field applies free-stream conditions across the entire domain. The initial velocity of 291.68 m/s is calculated using the following formula:

u = M \sqrt{γ R T}

where Mach number $M = 0.8395$ , ratio of specific heats $γ = 1.4$ , the specific gas constant for air $R$ = 287 J/kg-K and temperature $T$ = 300 K. As the turbulent viscosity ratio was set to 0.2105 on the freestream boundary, this value is also applied as an initial condition.

Edit the Continua > Fluid > Initial Conditions node and set the following properties:


Node	Property	Value
Turbulent Viscosity Ratio	Value	0.2105
Velocity	Method	Composite
Composite > X Component	Value	291.68*cos(${AoA})
Composite > Z Component	Value	291.68*sin(${AoA})

Save the simulation.