| タイトル | Computation of the steady viscous flow over a tri-element 'augmentor wing' airfoil |
| 著者（英） | Andrews, A. E.; Pulliam, T. H.; Chaussee, D. S.; Sorenson, R. L.; Kutler, P.; Lasinski, T. A. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1982-01-01 |
| 言語 | eng |
| 内容記述 | The augmentor wing consists of a main airfoil with a slotted trailing edge for blowing, and two smaller aft airfoils which shroud the jet. This configuration has been modeled for numerical simulation by a novel discretization procedure which generates four separate grids: three surface-oriented airfoil grids and one outer free-stream grid. Grid lines and slopes are continuous across boundaries, so grid overlap at common boundaries provides boundary information without interpolation. A two-dimensional unsteady thin-layer Navier-Stokes code is used to calculate the flow for the no-blowing case at freestream Mach number = 0.7, Re = 12,600.000, and angles-of-incidence = 1.05 deg. Qualitative agreement with experimental data indicates the utility of this procedure in the analysis of multi-element configurations. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 82A17735
AIAA PAPER 82-0021 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/412598 |
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