| タイトル | A comparison of interactive boundary-layer and thin-layer Navier-Stokes procedures |
| 著者（英） | Chang, K. C.; Cebeci, T.; Mehta, U. |
| 著者所属（英） | NASA Ames Research Center|Douglas Aircraft Co., Inc. |
| 発行日 | 1986-01-01 |
| 言語 | eng |
| 内容記述 | Numerical procedures for solving the thin-shear-layer Navier-Stokes equations and for the interaction of solutions to inviscid and boundary-layer equations are described and evaluated. To allow appraisal of the numerical and fluid dynamic abilities of the two schemes, they have been applied to one airfoil as a function of angle of attack at two slightly different Reynolds numbers. The NACA 0012 airfoil has been chosen because it allows comparison with measured lift, drag, and moment and with surface-pressure distributions. Calculations have been performed with algebraic eddy-viscosity formulations, and they include consideration of transition. The results are presented in a form that allows easy appraisal of the accuracy of both procedures and of the relative costs. The interactive procedure is computationally efficient but restrictive relative to the thin-layer Navier-Stokes procedure. The latter procedure does a better job of predicting drag than does the former. In both procedures, the location of transition is crucial for accurate or detailed computations, particularly at high angles of attack. When the upstream influence of pressure field through the shear layer is important, the thin-layer Navier-Stokes procedure has an edge over the interactive procedure. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 87A11785 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/381821 |
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