Numerical simulation analysis for grid convergence and code validation studies using the NASA CRM wing-body-nacelle-pylon configuration

Jong Lee, University of Illinois at Urbana-Champaign

Usage Details

For accurate numerical flow simulation, the use of numerical models and methods has been accuracy guaranteed is necessary. As using dense grid, the detailed numerical flow simulation is possible. CFD simulation with huge grid was not performed actively because of computer performance and calculation resource problem. However, due to advances in computer performance and parallel computing techniques, the numerical flow analysis using big size grid became possible. The size of the grid used by CFD researchers is increasing more and more. Therefore, the parallel computation capability on CFD code is required. The size of the grid used by the AIAA CFD Workshop is increasing. The maximum grid size used in the 2012 5th Drag Prediction Workshop (DPW) was 100 million, it will be expected to use about 200 million grid points in the 2016 DPW-6. In the present work, huge parallel CFD simulation will be performed using KFLOW on the flow field over the NASA CRM.