*
This computer program gives the blade-to-blade solution of the
two-dimensional, subsonic, compressible (or incompressible), nonviscous
flow problem for a circular or straight infinite cascade of tandem or
slotted turbomachine blades. The blades may be fixed or rotating.
The flow may be axial, radial, or mixed.*

*
The method of solution is based on the stream function using an
iterative solution of nonlinear finite-difference equations.
These equations are solved using two major levels of iteration.
The inner iteration consists of the solution of simultaneous linear
equations by successive over-relaxation, using an estimated optimum
over-relaxation factor. The outer iteration then changes the
coefficients of the simultaneous equations to correct for
compressibility.*

*
The program input consists of the basic blade geometry, the meridional
stream channel coordinates, fluid stagnation conditions, weight flow
and flow split through the slot, and inlet and outlet flow angles.
The output includes blade surface velocities, velocity magnitude and
direction throughout the passage, and the streamline coordinates.
(NASA Lewis Research Center)*

This program was released by NASA through COSMIC as LEW-10743. The italicized text above is from the official NASA release.

- Go to the page of references for the Tandem Blade program.
- Download tandem.zip, containing the original source code and the source code partially converted to modern Fortran.