Abstract
A fractional step numerical procedure for the solution of inviscid two-dimensional blade-to-blade flow problems is presented. A predictor-corrector McCormack explicit scheme is employed in order to advance the solution within each fractional step. The procedure is enhanced with local time stepping and second order artificial dissipation. Results are presented for channel as well as cascade flows in the subsonic and the transonic flow regimes.
| Original language | English (US) |
|---|---|
| Pages | 13-18 |
| Number of pages | 6 |
| State | Published - 1988 |
| Event | Flows in Non-Rotating Turbomachinery Components - Chicago, IL, USA Duration: Nov 27 1989 → Dec 2 1989 |
Conference
| Conference | Flows in Non-Rotating Turbomachinery Components |
|---|---|
| City | Chicago, IL, USA |
| Period | 11/27/89 → 12/2/89 |
All Science Journal Classification (ASJC) codes
- General Engineering
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