The LAVA computational fluid dynamics solver

The Launch Ascent and Vehicle Aerodynamics (LAVA) solver, developed at NASA Ames Research Center, is introduced. The focus of the solver is Computational Fluid Dynamics (CFD), but it also features auxiliary modules for Conjugate Heat Transfer (CHT) and Computational Aero-Acoustics (CAA) capabilities. LAVA is designed to be grid-flexible, i.e., it can handle Cartesian, block-structured curvilinear or unstructured grids either in stand-alone or by coupling different grid types through an overset interface. A description of the spatial discretizations utilized for each grid type, along with the available explicit and implicit time-stepping schemes, is provided. An overset grid coupling procedure of Cartesian and unstructured mesh types, as well as the CHT and CAA capabilities are outlined. Several NASA mission related applications are highlighted: pressure, thermal and acoustic analyses of the geometrically complex launch environment; steady and unsteady ascent aerodynamics; and plume-induced flow separation analyses of heavy lift launch vehicles. Two validation studies from NASA’s fundamental aeronautics program are presented: MIT’s fixed-wing D8 “double-bubble” aircraft, and the 1st AIAA Sonic Boom Prediction Workshop test cases.