Transonic Navier-Stokes flow computations over wing-fuselage geometries

被引：0

作者：

机构：

[1] Agrawal, S.

[2] Vatsa, V.N.

[3] Kinard, T.A.

来源：

Agrawal, S. | 1600年 / 30期

关键词：

Aerodynamics - Computer aided analysis - Geometry - Numerical methods - Wings;

D O I：

暂无

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学科分类号：

摘要：

Transonic Navier-Stokes solutions were obtained for a transport (RAE) wing-fuselage configuration. A C-O grid topology was used since it has the advantage of requiring strong clustering one coordinate direction for resolving the boundary layers developing on both wing and fuselage surfaces. A grid refinement study was also conducted to assess the effect of artificial dissipation models (SDM and MDM), and truncation errors on the numerical solutions. Based on this study, it was concluded that the fine grid solutions were gridconverged. Computed results using MDM on the fine grid compared best with the experimental data.

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