Inviscid Bump in a Channel
Inviscid Supersonic Wedge
Inviscid ONERA M6
Laminar Flat Plate
Turbulent Flat Plate
Transitional Flat Plate
Transitional Flat Plate for T3A and T3A-
Turbulent ONERA M6
Epistemic Uncertainty Quantification of RANS predictions of NACA 0012 airfoil
Non-ideal compressible flow in a supersonic nozzle
Unconstrained shape design of a transonic inviscid airfoil at a cte. AoA
Constrained shape design of a transonic turbulent airfoil at a cte. CL
Constrained shape design of a transonic inviscid wing at a cte. CL
Shape Design With Multiple Objectives and Penalty Functions
Unsteady Shape Optimization NACA0012
Unconstrained shape design of a two way mixing channel
Laminar Backward-facing Step
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Upon completing this tutorial, the user will be familiar with performing a simulation of internal, laminar, incompressible flow in a channel over a backward-facing step. Consequently, the following capabilities of SU2 will be showcased in this tutorial:
- Steady, 2D, laminar, incompressible, Navier-Stokes equations
- Flux Difference Splitting (FDS) convective scheme in space (2nd-order, upwind)
- Euler implicit time integration
- Inlet, outlet, and no-slip wall boundary conditions
The intent of this tutorial is to introduce the capability for prescribing inlet condition data from a file instead of assuming uniform conditions. The new options needed for this feature will be explained. We will also compare velocity profile results against numerical results from literature.
The resources for this tutorial can be found in the incompressible_flow/Inc_Laminar_Step directory in the tutorial repository. You will need the configuration file (lam_backwardstep.cfg) and the mesh file (mesh_backward_step_481x65.su2).
The following tutorial will walk you through the steps required when solving for the flow over a backward-facing step using the incompressible solver in SU2. It is assumed you have already obtained and compiled the SU2_CFD code for a serial computation. If you have yet to complete these requirements, please see the Download and Installation pages.
The backward-facing step is another common test case for CFD codes. Although the geometry is very simple, the flow can feature interesting separation regions, which also makes it an ideal candidate for testing numerical boundary conditions as well. There are many studies in the literature for the backward-facing step. In this tutorial, we will focus on the laminar problem found in the following reference: D. K. Gartling, A test problem for outflow boundary conditions - flow over a backward-facing step. Int. J. Numer. Methods Fluids 11 953 (1990).
This problem will solve for the incompressible flow over the backward-facing step with the following conditions that are set to match the Reynolds numbers of 400 and 800 based on a channel height of 1 m:
- Density (constant) = 1.0 kg/m^3
- Outlet Pressure = 0.0 N/m^2
- Viscosity (constant) = 0.0025 kg/(m-s) for Re 400, 0.00125 kg/(m-s) for Re 800
The flow enters the domain from the inlet boundary on the upper half of the channel height in the positive x-direction with the following velocity profile: u(y) = 24.0 * y * (0.5 - y) for 0 <= y <= 0.5.
The computational mesh for the backward-facing step is composed of quadrilaterals with 485 nodes in the x-direction and 65 nodes in the y-direction. The spacing of the nodes is uniform in the x- and y-directions. The domain is 15 channel heights in width. We will impose that the upper and lower boundaries of the channel are no-slip walls.
The upper half of the left vertical boundary of the domain is the inlet, while the bottom half is a no-slip wall representing the step face. Rather than simulate the upstream portion of the channel leading up to the step, we will impose the developed velocity profile given above as an inlet condition. A typical pressure outlet condition is imposed at the downstream boundary of the domain.
Configuration File Options
The necessary config options for imposing velocity profiles from file will be covered here. First, specify the inlet marker as we typically do for a uniform velocity inlet in incompressible flow. In order to override the uniform velocity inlet behavior, you should add two new options:
% Read inlet profile from a file (YES, NO) default: NO SPECIFIED_INLET_PROFILE= YES % % Input file for a specified inlet profile (w/ extension) INLET_FILENAME= inlet_step.dat % % Inlet boundary marker(s) with the following formats (NONE = no marker) % Incompressible: (inlet marker, temperature, velocity magnitude, flow_direction_x, % flow_direction_y, flow_direction_z, ... ) where flow_direction is % a unit vector. MARKER_INLET= ( inlet, 0.0, 1.0, 1.0, 0.0, 0.0 )
The first is a switch to activate the inlet profile mode with
SPECIFIED_INLET_PROFILE= YES (
NO by default). Once activated, SU2 will look for a file in the working directory with the name given in the option
INLET_FILENAME. Here, we have given the custom name
inlet_step.dat, but by default SU2 will look for a file named
Now, we create the inlet profile file, which has a simple ASCII format. Open a new file named
inlet_step.dat in the working directory and copy into place the following:
NMARK= 1 MARKER_TAG= inlet NROW= 33 NCOL= 6 0.000000 0.000000 1.000000 0.000000 1.000000 0.000000 0.000000 0.015625 1.000000 0.181641 1.000000 0.000000 0.000000 0.031250 1.000000 0.351562 1.000000 0.000000 0.000000 0.046875 1.000000 0.509766 1.000000 0.000000 0.000000 0.062500 1.000000 0.656250 1.000000 0.000000 0.000000 0.078125 1.000000 0.791016 1.000000 0.000000 0.000000 0.093750 1.000000 0.914062 1.000000 0.000000 0.000000 0.109375 1.000000 1.025391 1.000000 0.000000 0.000000 0.125000 1.000000 1.125000 1.000000 0.000000 0.000000 0.140625 1.000000 1.212891 1.000000 0.000000 0.000000 0.156250 1.000000 1.289062 1.000000 0.000000 0.000000 0.171875 1.000000 1.353516 1.000000 0.000000 0.000000 0.187500 1.000000 1.406250 1.000000 0.000000 0.000000 0.203125 1.000000 1.447266 1.000000 0.000000 0.000000 0.218750 1.000000 1.476562 1.000000 0.000000 0.000000 0.234375 1.000000 1.494141 1.000000 0.000000 0.000000 0.250000 1.000000 1.500000 1.000000 0.000000 0.000000 0.265625 1.000000 1.494141 1.000000 0.000000 0.000000 0.281250 1.000000 1.476562 1.000000 0.000000 0.000000 0.296875 1.000000 1.447266 1.000000 0.000000 0.000000 0.312500 1.000000 1.406250 1.000000 0.000000 0.000000 0.328125 1.000000 1.353516 1.000000 0.000000 0.000000 0.343750 1.000000 1.289062 1.000000 0.000000 0.000000 0.359375 1.000000 1.212891 1.000000 0.000000 0.000000 0.375000 1.000000 1.125000 1.000000 0.000000 0.000000 0.390625 1.000000 1.025391 1.000000 0.000000 0.000000 0.406250 1.000000 0.914062 1.000000 0.000000 0.000000 0.421875 1.000000 0.791016 1.000000 0.000000 0.000000 0.437500 1.000000 0.656250 1.000000 0.000000 0.000000 0.453125 1.000000 0.509766 1.000000 0.000000 0.000000 0.468750 1.000000 0.351562 1.000000 0.000000 0.000000 0.484375 1.000000 0.181641 1.000000 0.000000 0.000000 0.500000 1.000000 0.000000 1.000000 0.000000
NMARK defines how many inlet markers will be described in the file (multiple markers are possible). For each marker, we start the specification with giving the marker string name, which should match the value in the grid and config file, with
MARKER_TAG. Then the number of rows and columns to be prescribed should be defined with
NCOL. Currently, only a 1-to-1 point matching of the values in the profile with the vertices on the marker is possible (interpolation will be added in the future), meaning that
NROW should be equal to the number of nodes on the boundary marker. Each row in the set defines the inlet data for one vertex on the boundary. Note that the ordering of the rows does not matter, as the points are matched based on the postion coordinates given.
NCOL will be problem dependent. Here, since we have a 2D problem, the columns represent the following variables: x, y, temperature, velocity magnitude, x-component of flow direction unit vector, y-component of flow direction unit vector. In 3D, one would have x, y, z, temperature, velocity magnitude, x-component of flow direction unit vector, y-component of flow direction unit vector, z-component of flow direction unit vector. Note that inlet profiles are also available for use with the compressible solver, and the values for temperature and velocity magnitude here will be replaced by either the total temperature and total pressure or the density and velocity magnitude, depending on your compressible inlet type. For turbulent calculations, the turbulence variables can also be specified by including additional columns (1 for S-A, 2 for k and omega in SST, for example).
Lastly, to ease the process of generating the correct inlet profile format, SU2 can generate a template for you automatically. First, prepare the
MARKER_INLET as if specifying uniform inlet conditions. Set
SPECIFIED_INLET_PROFILE= YES and execute
SU2_CFD. If SU2 does not find an inlet profile file in the working directory, it will generate one for you in the proper format for the case at hand and fill it with the uniform inlet data. This file can then be used as a template to swap in your own inlet profile data.
The backward-facing step simulation will execute relatively quickly on a single workstation or laptop in serial. To run this test case, follow these steps at a terminal command line:
- Move to the directory containing the config file (lam_backwardstep.cfg) and the mesh file (mesh_backward_step_481x65.su2). Make sure that the SU2 tools were compiled, installed, and that their install location was added to your path.
Run the executable by entering
$ SU2_CFD lam_backwardstep.cfg
at the command line.
- SU2 will print residual updates with each iteration of the flow solver, and the simulation will terminate after reaching the specified convergence criteria.
- Files containing the results will be written upon exiting SU2. The flow solution can be visualized in ParaView (.vtk) or Tecplot (.dat for ASCII).
Results are given here for the SU2 solution of incompressible laminar flow over the backward-facing step. The velocity profiles show excellent agreement with the results from Gartling.
Figure (2): Streamlines for the Re = 800 backward-facing step case colored by non-dim. velocity magnitude.
Figure (3): Comparison of SU2 non-dim. x-velocity profiles at x = 7 m and x = 15 m with those of Gartling.