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High-order accuracy numerical simulation of DLR-F6 wing-body configuration
Received date: 2014-09-07
Revised date: 2014-12-29
Online published: 2015-01-07
Supported by
National Key Basic Research Program of China (2014CB744803)
Based on the Reynolds-averaged Navier-Stokes (RANS) equations and structured grid technology, the fifth-order weighted compact nonlinear scheme (WCNS) and shear stress transport (SST) turbulence model are adopted to conduct a high-order numerical simulation of DLR-F6 wing-body configuration, for the purpose of validating the ability of WCNS in the simulation of typical transport configuration at transonic speed. The grid convergence study is performed with coarse, medium and fine grid systems, the effects of grid density on the simulation of DLR-F6 wing-body configuration are studied from aerodynamic characteristics, pressure distribution and flow pattern on the surface. The variation of aerodynamic characteristics with angles of attack is performed with the medium grid. Compared to the experimental data, CFL3D and TRIP results, the numerical results indicate that the grid density mainly affect the location of shock wave and pressure drag coefficient, and slightly affect the size of separation zone at the wing-body juncture. The numerical accuracy is significantly improved with high-order numerical method and the discrepancy of pitching moment coefficients between numerical data and experimental data needs further study.
WANG Yuntao , SUN Yan , WANG Guangxue , ZHANG Yulun , LI Wei . High-order accuracy numerical simulation of DLR-F6 wing-body configuration[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015 , 36(9) : 2923 -2929 . DOI: 10.7527/S1000-6893.2014.0362
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