Centered and Upwind Multigrid Turbulent Flow Simulations of Launch Vehicle Configurations
Journal of Spacecraft and Rockets
The paper discusses results obtained with a finite-volume code that simulates viscous, turbulent flows for 3-D, adaptive, unstructured meshes. The implementation uses a cell-centered, face-based data structure. A fully explicit, second-order accurate, five-stage, Runge-Kutta time stepping scheme is used to perform the time marching of the flow equations. Spatial discretization of the Reynolds-averaged Navier-Stokes equations can be performed with second-order centered or upwind schemes.
... nd schemes. Automatic grid refinement routines are considered to adapt the original mesh. A sensor based on density gradients selects the volumes to be refined. The code is able to handle tetrahedra, hexahedra, wedges, and pyramids. A full multigrid scheme is available to accelerate convergence to steady state. Coarse grid levels are constructed through an agglomeration procedure. One-and two-equation turbulence models are implemented to include the turbulent effects into the numerical formulation. The mentioned features integrated in one single code allow the Brazilian aerospace program to simulate complex flow conditions for sounding rockets and satellite launch vehicles with accuracy and reasonable computational resources. Good agreement with theoretical or experimental results is obtained with the present numerical tool. method on 3-D unstructured meshes to simulate turbulent viscous flows over typical aerospace configurations. The numerical tool was developed by the CFD group at Instituto de Aeronáutica e Espaço (IAE) to aid the design of aerospace vehicles. One such aerospace configuration of interest to IAE is the first Brazilian Satellite Launch Vehicle (VLS). The VLS launcher is composed of a Presented as Paper 5384 at the 22nd AIAA Applied Aerodynamics