Chen J.,China Aerodynamics Research And Development Center |
Chen J.,Computational Aerodynamics Institute |
Zhang Y.,China Aerodynamics Research And Development Center |
Zhang Y.,Computational Aerodynamics Institute |
And 4 more authors.
Journal of Aircraft | Year: 2015
Numerical investigations of the DLR F11 high-lift configuration from the 2nd AIAA High-Lift Prediction Workshop are performed with the in-house solver MFlow. The solver is based on a cell-centered finite-volume method and is capable of handling various element types. Hexahedral grids and hybrid grids are used in the simulations. Gridconvergence properties, polar line, and pressure distributions are analyzed and compared with experimental data. A nearly linear convergence property is achieved with grid refinement for configuration 2, which is the most simplified configuration of the experiment model. When including slat and flap brackets (configuration 4), results are improved compared to the simplified configuration. However, delayed stall and larger maximum lift coefficient compared with experiment are found for high-Reynolds-number computations. The rotation correction of Spalart-Allmaras model does not lead to obvious improvement at high angles of attack. The effects of Reynolds number are qualitatively captured by the simulations. The inclusion of pressure-tube bundles causes loss of lift near stall and has little influence on predictions at lower angles of attack. The solver shows good agreement with experiment at lower angles of attack, but more attention is needed at angles of attack near and beyond stall. © 2015 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.