An Alternating-Direction-Implicit Solution of Subsonic Cascade FLow.
Interim rept. 15 Jan-30 Sep 75,
AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OHIO
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Two numerical methods -- alternating-direction-implicit ADI and Gauss-Seidel -- of solving the partial differential equations of subsonic cascade flow are compared. The ADI method was found to be slower and to offer no advantages of accuracy or computer storage. A stability analysis disclosed the existence of a maximum allowable integration step for the ADI algorithm. Implementation of the ADI method and the inclusion of boundary conditions are described and the computer times required for each facet of the ADI iteration are reported. The study concludes that the ADI algorithm is not a viable appraoch to this type of problem. Author
- Fluid Mechanics
- Jet and Gas Turbine Engines