Numerical Investigations of the NASA Common Research Model with Aeroelastic Twist

摘要

Numerical investigations of the NASA Common Research Model from the 6th AIAA CFD Drag Prediction Workshop are performed with in-house solver MFlow. The solver is based on a cell-centered finite volume method and is capable of handling various element types. Hybrid grids supplied by the committee and generated in-house are used in the simulations. Grid convergence properties, polar lines, and pressure distributions are analyzed and compared with experimental data. A nearly linear convergence property is achieved with grid refinement for own-generated hybrid grids. The drag increment due to nacelle and pylon is well predicted. As angle of attack increases, the simulations with the original Spalart-Allmaras or shear-stress transport model exhibit a large side-of-body separation, whereas the results obtained with quadratic constitutive relation present a negligible separation bubble, which is more reasonable judging from experimental data. The solver shows good agreement with experiment. The predictions are much improved with the static aeroelastic effect considered in simulations.