For the k- ω SSTm model, excellent agreement is also obtained with Flow360 integrated loads closer matching CF元D data. The SA-RC model shows good agreement for the lift coefficient with FUN3D, whereas the drag coefficient is in between the CF元D and FUN3D data. #įor the SA turbulence model, the Flow360 results agree very well with FUN3D integrated loads. Table 6.2.2 Comparison of integrated loads between different CFD solvers for the NACA4412 aerofoil using the SA, SA-RC and k- ω -SSTm turbulence models. Note the OVERFLOW code uses the baseline k- ω SST model, whereas the k- ω SSTm model is used by CF元D, FUN3D and Flow360. Numerical Results #įirstly, the integrated are compared between Flow360, CF元D, FUN3D, OVERFLOW for the SA, SA-RC and k- ω -SSTm turbulence models, shown in Table 6.2.2. The Flow360Mesh.json and Flow360.json files are provided for the SA model simulations (compatible with the modified NACA4412 grid for number of boundaries and boundary names). For the majority of simulations, 1e-12 residual convergence was obtained for the flow residuals and 1e-10 for the turbulence residuals. To ensure deep convergence of the simulaitons, the CFL number was reduced to a value of 20, along with reducing the Jacobian update frequency from 4 to 1 towards the end of the simulations, although the impact on the integrated loads was minimal. The simulations were performed using a CFL number of 200 ramped up over the initial 2000 iterations. # Table 6.2.1 Solver inputs for the NACA4412 trailing edge separation study. 6.2.2 Summary of case boundary conditions and conditions for the NACA4412 trailing edge separation study. 6.2.2 shows the case layout in detail, whereas the solver inputs are summarized in Table 6.2.1.įig. For the k- ω SSTm calculations a turbulent viscosity ratio of 0.009 was used. Fully-turbulent calculations were performed with the ratio of the freestream value of the SA turbulence field variable (relative to laminar) set to 3, set in Flow360 as a turbulent viscosity ratio of 0.210438. A reference temperature of 297.778K was used. The study was performed for an angle of attack of 13.87 degrees. The flow conditions were set to 1.52 million Reynolds number and a Mach number of 0.09. #Ī farfield Riemann boundary condition is used which is placed 100 chords away from the airfoil. 6.2.1 Far-field and near-field views of the grid used for the NACA4412 trailing edge separation study. The grid far-view and near-view is shown in Fig. The grid used in Flow360 was modified for the names and number of boundaries, and is available here A detailed grid convergence study is not performed here. The second finest grid (897 by 257 points) is used to perform direct comparisons with CF元D and FUN3D on the same grid. Simulation setup #Ī single C-Topology grid is used, available at the NACA4412 case grid download page of the TMR website. While primarily being a validation case for capturing the trailing edge separation, certain model implementation verification can be performed by comparing the results with other CFD codes. The experimental data includes surface pressure data as well as velocity profiles near the trailing edge of the airfoil. The case is part of the NASA Turbulence Modelling Website and has also been evaluated by other CFD solvers such as OVERFLOW in Jespersen et al. Three different turbulence models are evaluated for this case: SA, SA-RC and k- ω SSTm. The main purpose of this case is validation of the Flow360 solver against experimental data and other CFD solvers, primarily CF元D. 2D NACA 4412 Airfoil Trailing Edge Separation # 6.2.1. STEP Format CAD Import for Automated MeshingĦ.2. CGNS Mesh Format and Multizone Interface ConnectivityĨ.1.7. TU Berlin TurboLab Stator simulation using periodic boundary conditionsĨ.1.6. Conjugate Heat Transfer for Cooling Finsħ.9. Calculating Dynamic Derivatives using Sliding Interfacesħ.8. Time-accurate RANS CFD on a propeller using a sliding interface: the XV-15 rotor geometryħ.6. Blade Element Theory using the XV-15 rotorħ.5. RANS CFD on 2D High-Lift System Configuration Using the Flow360 Python Clientħ.4. Non-Dimensionalization and Integrated Loads Post-Processing in Flow360ħ.3. Geometry Modeling and Preparation for Automated Meshing: An Example of the ONERA M6 Wingħ.2. Scale-Resolving Simulations Past a Circular Cylinderħ.1. XV-15 Rotor Blade Analysis using the Blade Element Disk MethodĦ.11. Drag Prediction of Common Research ModelĦ.9. High Lift Common Research Model (HL-CRM)Ħ.7. 2D NACA 4412 Airfoil Trailing Edge SeparationĦ.6. Propeller Models and Rotational Volume ZonesĦ.2.
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