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RANSFOIL is a console program to calculate airflow field around an isolated airfoil in low-speed, subsonic, transonic or supersonic regime by numerically solving the Reynolds averaged Navier-Stokes (RANS) equations using mature computational fluid dynamics (CFD) method. As postprocess results, the aerodynamic parameters of the airfoil, e.g., lift coefficient and drag coefficient, can be integrated from the airflow distribution near wall boundary. In addition, the coupling between airflow and heat transfer and the effect of surface roughness on near wall flow are considered by this program, it can be used for engineering calculation of the friction drag and heat transfer coefficients on airfoil surface. RANSFOIL reads coordinates data from a 1D XYZ file which describes the grid points or control points on airfoil as only input, then outputs grid and solution files in 2D PLOT3D format to record grid coordinates and airflow data and a report file to show aerodynamic parameters.
Features
- use GNU Autotools to deploy on Linux and Windows platforms
- two execution modes, an interactive mode and a batch mode
- generate the airfoil profile from Selig format control points
- built-in structured mesh generator via extruding the airfoil profile
- a robust pressure-based finite volume solver
- the air property can be incompressible in low-speed regime or compressible at high Mach number
- three mature turbulence model, standard k-epsilon, S-A and SST k-omega
- two methods as near wall treatment model, enhanced wall function and low Reynolds number model
- model smooth or rough airfoil surface
- report aerodynamic parameters in large range from low-speed to supersonic
- abundant export files to describe the results
- provide application program interface in a shared library which can be called using Fortran and C language
Project Samples
