Transonic Flow Around Compressor Rotor Blade Elements. Volume II. Digital Program User's Manual.
Final rept. 1 Dec 71-30 Jun 73,
GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV
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A computer program to analyze steady-state transonic flow in turbomachinery components has been developed. The time-dependent partial differential system of equations is approximated by the MacCormack finite-difference algorithm. The program is operational for two-dimensional compressor cascades or quasi-three-dimensional rotors including radius and stream surface thickness variations. A hybrid method of characteristics is used to impose the boundary constraints upon the flow field. Flow field periodicity is used at the free surface boundaries. Output consist of a flow field description and mixed-out properties of the flow at the exit. Author
- Computer Programming and Software
- Fluid Mechanics
- Jet and Gas Turbine Engines