HEMLAB Algorithm Applied to HIOCFD Delta Wing and CFD_OTC1 Missile

In this study, the delta wing case proposed at the International Workshop of High Order Computational Fluid Dynamics (HIOCFD) Methods and the CFD_OTC1 missile test case were studied numerically. The study was executed by using HEMLAB algorithm in order to predict the flow characteristics and aerodynamics loads. The HEMLAB algorithm is a compressible Reynolds Averaged Navier-Stokes (RANS) solver with a highly efficient edge based data structure and it is integrated with an anisotropic mesh adaptation library in order to further improve its computational efficiency. The anisotropic mesh refinement method was based on the INRIA pyAMG software which improves the mesh resolution in high gradient regions. The fully coupled second-order negative Spalart-Allmaras turbulence model was used to model the turbulence effects. The numerical algorithm was initially validated for the delta wing case at a low Reynolds number with a high angle of attack. The computed lift and drag coefficients were used to validate the algorithm. Different mesh adaptation approaches and numerical ux evaluations were investigated in detail. Then the numerical algorithm was applied to the CFD_OTC1 missile at high angle of attacks to predict the moment and force coefficients with the vortical structures around the missile body. The numerical calculations with anisotropic mesh adaptation indicated significant improvements compared to xed mesh calculations.