Investigation of Benchmark Turbulent Flows

Abstract

Several benchmark test cases have been implemented over the last few years in furtherance of providing reference results for turbulent flows with high Reynolds number. With these test cases, information regarding the behavior study of accuracy and the solution methods of the available codes that were employed for solving the Reynolds-averaged Navier-Stokes equations (RANS) were investigated. The relevant benchmark test cases that are admissible to this thesis are: - 2D Finite Flat Plate, - 2D NACA 0012 Airfoil, - 3D Modified Bump, - 3D Hemisphere Cylinder, and - 3D ONERA M6 Wing. The suitable parameters for all the test cases are accessed from the "Turbulence Modeling Resource" (TMR) website [1] of National Aeronautics and Space Administration (NASA). The thesis contains a thorough analysis of the test cases and it is done by first extracting the meshes from the website through a FORTRAN code by which a sequence of meshes ranging from coarse to fine is generated. These meshes are excerpted to a data format that can be used for computations by the DLR-TAU (Triangular Adaptive Upwind) code [2]. The TAU code is a software for performing numerical computations especially with flows around complex geometries. Chap. 4 addresses the solution methodologies, all of which are fed into the code. Furthermore, RANS equations are solved for these meshes and the results from the computations are studied focusing on its behavioral properties.