This software package allows you to efficiently simulate three-dimensional (3-D) flows on multiblock, structured grids. It consists of a general purpose flow solver for the solution of the Euler or the Navier-Stokes equations on stationary, as well as on moving / deforming grids. Further included are tools for pre-processing of the grids, generation of the initial solution and for post-processing. The resulting plot files can be visualized by the wide-spread commercial tool Tecplot.
Description of the numerical methods used and the capabilities of an earlier version of Snas3D can be found in this conference paper.
Executables of the flow solver and tools, examples of input files and user's manual for Windows 7-10 platforms (64-bit, single processor) or for GNU/Linux platforms (compiled & tested on Ubuntu 18.04). The programs are completely free for non-commercial use and for evaluation purposes. Other uses require the purchase of a license, possible options are described further below. If you happen to find any problem with the software, please let us know. And if you are interested to learn more about the numerical methods built into the flow solver, you might consider buying the CFD book.
Example flow cases (grids, input files):
Free tool for the generation of 3-D, viscous or inviscid, H-type grids in axial compressor or turbine passages thg3d.zip (for Windows 7-10) or thg3d_linux.tgz (for GNU/Linux). This tool was employed to generate the grid for the above turbine guide vane example.
For commercial purposes or for more extended applications of the software, we offer the following purchase options:
Please, feel free to ask us for a quote regarding any of the above options.
The data for this case were taken from: Zeschky, J.: Experimentelle Untersuchung der dreidimensionalen reibungsbehafteten Rotorströmung einer axialen Kaltluftturbine. PhD Thesis, RWTH Aachen, Germany, 1991. The following pictures show the H-type grid (160x48x48 cells), the (unsteady) convergence history, flow inside the passage, and finally a comparison with experimental data at mid-height:
The following pictures present the results obtained by Snas3D for the ONERA M6 test case. It constitutes transonic, turbulent flow past a 30° swept wing at Mach 0.8395, angle of attack 3.06° and Reynolds number of 11.72 million:
The video shows simulation of the ignition and the burnout of a small solid rocket motor. The time-accurate 3-D flow was computed using grid composed of 128 blocks and 220'416 cells. The grid is expanding as the solid fuel burns off:
This is one of the simulations described in the above mentioned conference paper.
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