This program provides a nice interactive environment in which to learn about compressor and turbine cascade aerodynamics. The flow is computed using a panel method in which vortex singularities are distributed along the airfoil. A large number of commonly used airfoils are known to the program and their geometry can be saved to disk.
Main data input screen in which cascade parameters are input.
Results screen, plots of velocity distributions and pressure coefficient. A mouse can be used to interactively investigate the flow field.
The plots below show the velocity vectors on the airfoils, rotated by 90 degrees. Some streamlines, interactively drawn during program execution, are also shown.
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NACA 65-512 airfoil compressor cascade at solidity=1 |
NACA A3K7 4020 turbine cascade at solidity=1 |
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This code is freely available for download. Unpack cfoil.zip somewhere on a Windows 3.1 or later system.
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