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Aerodynamic and Aerothermal Simulations of Mars Concept Vehicles Using Overset DPLRNASA's Descent System Studies (DSS) Program is studying various concept vehicles to enable landing of heavy payloads on the surface of Mars. While it is desirable to run high-fidelity CFD simulations to accurately assess the aerodynamic and aerothermal effects of various design changes during EDL, it is usually difficult to quickly generate high-quality grids suitable for such analyses. One approach to address this bottleneck in mesh generation is through the use oversetting grids. Although the overset approach is efficient and powerful in solving partial differential equations on complex geometries, new users often find it challenging to apply overset concepts for their simulations. For example, generating hyperbolic grids with sufficient overlap; priority in hole-cutting on multiple overlapping grids; and fixes to assemble overlapping viscous grids at the body surface. The objective of this presentation is to introduce a simple process that combines the advantages of near-body, point-matched, structured grids with oversetting background grids suitable for grid alignment. This approach allows for grids that can be sequenced, reclustering of mesh spacing at the wall, and grid alignment with the bow shock. The current methodology is tested on a Mid-L/D configuration using the overset DPLR code.


Document ID
20190030276
Acquisition Source
Ames Research Center
Document Type
Presentation
Authors
Tang, Chun (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 28, 2019
Publication Date
August 26, 2019
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
ARC-E-DAA-TN72528
Meeting Information
Meeting: Thermal & Fluids Analysis Workshop (TFAWS 2019)
Location: Hampton, VA
Country: United States
Start Date: August 26, 2019
End Date: August 30, 2019
Sponsors: NASA Langley Research Center
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Overset Grids
DPLR

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