| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 763226 | Computers & Fluids | 2006 | 7 Pages |
Abstract
Steady transonic flows over a wing are calculated based on a hierarchical formulation where the potential flows are corrected due to the entropy and vorticity effects of shock waves and/or laminar boundary layers. Preliminary results are in agreement with standard Euler and Navier–Stokes calculations. The merits of the present approach are briefly discussed.
Related Topics
Physical Sciences and Engineering
Engineering
Computational Mechanics
Authors
Mohamed Hafez, Essam Wahba,