SU2 Training
Instead of writing a very detailed user manual, the approach has been taken to teach the various aspects of the SU2 code through a range of tutorials. These are ordered roughly by their complexity and how experienced with the code the user may need to be, noting that the more advanced tutorials may assume the user has already worked through the earlier ones. Each tutorial attempts to present new features of SU2 and contains explanations for the key configuration file options. For more information on the exact learning goals of a tutorial, these can be seen at the beginning of each.
( Keep an eye out here for coming video tutorials! )
Presentations
Introduction to SU2 [PDF]Introduction to the SU2 code structure [PDF]
Running SU2 [PDF]
SU2 2.0 Workshop Complete Recording [WMV]
Written Tutorials
Bump in a Channel
Steady, 2-D Euler
The intent of this tutorial is to introduce a simple, inviscid flow problem and to explain how boundary markers are used within SU2. This tutorial is especially useful for showing how an internal flow computation can be performed using the inlet and outlet boundary conditions.
Inviscid ONERA M6
Steady, 3-D Euler
Upon completing this tutorial, the user will be familiar with performing a simulation of external, inviscid flow around a 3-D geometry. The specific geometry chosen for the tutorial is the classic ONERA M6 wing. We will also discuss the details for setting up 3-D flow conditions and some of the multigrid options within the configuration file.
Laminar Flat Plate
Steady, 2-D, Laminar Navier-Stokes
The intent of this tutorial is to introduce a common viscous test case which is used to explain how different equation sets can be chosen in SU2. We also introduce details on the numerics and a new type of convergence criteria which monitors the change of a specific objective, such as lift or drag, in order to assess convergence.
Laminar Cylinder
Steady, 2-D, Laminar Navier-Stokes
The flow around a geometrically two-dimensional circular cylinder has often been used both as a validation and a legitimate research case. In this tutorial, we further discuss numerical method options, including how to activate a slope limiter for upwind methods.
Turbulent Flat Plate
Steady, 2-D Spalart-Allmaras
In this tutorial, we perform our first RANS simulation with the Spalart-Allmaras (SA) turbulence model. For verification we'll compare SU2 results against those from the NASA codes FUN3D and CFL3D. For validation we'll compare profiles of u+ vs. y+ against theoretical profiles of the viscous sublayer and log law region.
Turbulent ONERA M6
Steady, 3-D Spalart-Allmaras
This test case is for the ONERA M6 wing in viscous flow. The ONERA M6 wing was designed in 1972 by the ONERA Aeordynamics Department as an experimental geometry for studying three-dimensional, high Reynolds number flows with some complex flow phenomena (transonic shocks, shock-boundary layer interaction, separated flow). It has become a classic validation case for CFD codes due to the simple geometry, complicated flow physics, and availability of experimental data.
See Also: Problem workshop: SU2 as a high-fidelity analysis tool. [PDF]
Optimal Shape Design of a Rotating Airfoil
Steady, 2-D Euler, Adjoint
The following tutorial will walk you through the steps required when performing shape design for a 2-D airfoil geometry (initially the NACA 0012) which is rotating counter-clockwise in still air. This case makes use of the SU2 Adjoint capability to solve for sensitivities needed by a gradient-based optimizer.
Constrained Optimal Shape Design of a Fixed Wing
Steady, 3-D Euler, Adjoint
The following tutorial will walk you through the steps required when performing 3-D shape design using Free Form Deformation (FFD) tools for a 3-D fix wing geometry (initially the ONERA M6) at transonic speed in air.
See Also: Problem workshop: Design and optimization using SU2. [PDF]
High Speed Plasma
Steady, 3-D Chemically Reacting Navier-Stokes
This tutorial solves for viscous, chemically reacting flow in the vicinity of a shock wave in high temperature Argon gas. The plasma is modelled as a mixture of fluids assuming a continuum of species. The full set of governing equations comprises of the Navier-Stokes equations for the fluid-like behaviour of plasma, and relations describing the chemistry of non-equilibrium flows.
Inviscid Supersonic Wedge
Steady, 2-D Euler
This example uses a 2-D geometry which features a wedge along the solid lower wall. The intent of this tutorial is to introduce a simple, inviscid flow problem that will allow users to become familiar with using a CGNS mesh. This will require SU2 to be built with CGNS support, and some new options in the configuration file related to CGNS meshes will be discussed.
Adaptive Mesh Refinement
Gradient-Based and Goal-Oriented Adaptation
High-quality solutions require accurate resolution of flow features within the computational domain. Adaptive mesh refinement is a procedure by which the computational grid can be strategically refined to resolve these flow features using information from the direct and/or adjoint solutions. This problem deals again with the NACA 0012 airfoil in a transonic free stream and sharpens the shocks which form around the airfoil.
Task-Based Design Evaluation
Steady, 2-D Euler
This tutorial will perform design space exploration and optimal shape design using the SU2 class structure that enables just-in-time and redundant-free execution of analysis tasks. Only necessary analyses (mesh deformation, direct and adjoint solutions) will be called when needed by an optimizer. Additionally, all output data is organized into a file system to enable project restart and secondary post processing.
See Also: Problem workshop: Task-based design evaluation with SU2. [PDF]
