Computational framework for Launch, Ascent, and Vehicle Aerodynamics (LAVA)

The Launch Ascent and Vehicle Aerodynamics (LAVA) framework, developed at NASA Ames Research Center, is introduced. This technology originated from addressing some of the key challenges that were present during the re-design of the launch infrastructure at Kennedy Space Center. The solver combines C...

Full description

Saved in:
Bibliographic Details
Published in:Aerospace science and technology 2016-08, Vol.55, p.189-219
Main Authors: Kiris, Cetin C., Housman, Jeffrey A., Barad, Michael F., Brehm, Christoph, Sozer, Emre, Moini-Yekta, Shayan
Format: Article
Language:English
Subjects:
Aeroacoustics
Aerodynamics
Ascent
Cartesian
Computation
Computational fluid dynamics
Conjugate heat tranfer
Coupling
Curvilinear
Higher-order shock capturing
Hybrid grids
Immersed boundary methods
Launches
Lava
NASA
Overset methodology
Unstructured grids
Citations: Items that this one cites
Items that cite this one
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary:The Launch Ascent and Vehicle Aerodynamics (LAVA) framework, developed at NASA Ames Research Center, is introduced. This technology originated from addressing some of the key challenges that were present during the re-design of the launch infrastructure at Kennedy Space Center. The solver combines Computational Fluid Dynamics (CFD) capabilities with auxiliary modules, such as Conjugate Heat Transfer (CHT) and Computational Aero-Acoustics (CAA). LAVA is designed to be grid agnostic, i.e., it can handle block-structured Cartesian, generalized curvilinear overset and unstructured polyhedral grids either as stand-alone mode 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. The overset grid coupling procedure for Cartesian and unstructured mesh types, as well as the CHT and CAA capabilities is discussed in some detail. Several NASA mission related applications are also presented to demonstrate the capabilities for large-scale applications, such as pressure, thermal and acoustic analyses of the geometrically complex launch environment, steady and unsteady ascent aerodynamics, plume-induced flow separation analyses of heavy lift launch vehicles and aeroacoustic applications. In addition, two validation cases related to NASA aeronautics applications are presented: the 1st AIAA Sonic Boom Prediction Workshop test cases and a computational study of slat noise.
ISSN:1270-9638
1626-3219
DOI:10.1016/j.ast.2016.05.008