| タイトル | Three-layer interactive method for computing supersonic laminar separated flows |
| 著者（英） | Brandeis, J.; Rom, J. |
| 著者所属（英） | Technion - Israel Inst. of Tech.|NASA Ames Research Center |
| 発行日 | 1980-11-01 |
| 言語 | eng |
| 内容記述 | An interactive model for numerical computation of complicated two-dimensional flowfields including regions of reversed flow is proposed. The present approach is one of dividing the flowfield into three regions, in each of which a simplified mathematical model is applied: (1) outer, supersonic flow for which the full potential equation (hyperbolic) is used; (2) viscous, laminar layer in which the compressible boundary-layer model (parabolic) is used; and (3) recirculating flow modeled by the incompressible Navier-Stokes equations (elliptic). For matching of the numerical solutions in the three layers, two interaction models are developed: one for pressure interaction, the other for interaction between the shear layer and the recirculating flow. The uniform solution for the whole flowfield is then obtained by iteration of the local solutions under the constraints imposed by matching. The three-layer interactive model is used for solution of the flowfield past an asymmetric cavity. The method is shown to be capable of dealing with backflow without encountering problems at separation, characteristic to the boundary-layer approach. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 81A11576 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/419045 |
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