A multigrid overset grid flow solver with implicit hole cutting method

2007 ◽  
Vol 196 (9-12) ◽  
pp. 1701-1715 ◽  
Author(s):  
Wei Liao ◽  
Jinsheng Cai ◽  
Her Mann Tsai
Keyword(s):  
Overset Grid ◽  
Cutting Method ◽  
Flow Solver

An efficient parallel Chimera grid flow solver based on implicit hole cutting method

2018 ◽  
Author(s):  
Xiaodong Hu ◽  
Zhonghua Lu ◽  
Jian Zhang ◽  
Wu Yuan ◽  
Xiazhen Liu ◽  
...  
Keyword(s):  
Cutting Method ◽  
Flow Solver ◽  
Chimera Grid

Overset Grid Applications in Hypersonic Flow Using the DPLR Flow Solver

2008 ◽  
Author(s):  
David Boger ◽  
Ralph Noack ◽  
Adam Amar ◽  
Benjamin Kirk ◽  
Randolph Lillard ◽  
...  
Keyword(s):  
Hypersonic Flow ◽  
Overset Grid ◽  
Flow Solver ◽  
Grid Applications

scholarly journals Overset Grid Assembler and Flow Solver with Adaptive Spatial Load Balancing

2021 ◽  
Vol 11 (11) ◽  
pp. 5132
Author(s):  
Orxan Shibliyev ◽  
Ibrahim Sezai
Keyword(s):  
Relative Motion ◽  
Load Balance ◽  
Memory Usage ◽  
Overset Grid ◽  
Space Partitioning ◽  
Spatial Partitioning ◽  
Flow Solver ◽  
Flow Problems ◽  
3D Space ◽  
Connectivity Information

An overset mesh approach is useful for unsteady flow problems which involve components moving relative to each other. Since the generation of a single mesh around all components is prone to mesh stretching due to the relative motion of bodies, using the overset grid methodology, an individual mesh can be generated for each component. In this study, a parallel overset grid assembler was developed to establish connectivity across component meshes. Connectivity information was transferred to the developed parallel flow solver. The assembler uses multiple methods such as alternating digital tree and stencil walking to reduce the time spent on domain connectivity. Both the assembler and solver were partitioned spatially so that overlapping mesh blocks reside in the same partitions. Spatial partitioning was performed using a 3D space partitioning structure, namely octree, to which mesh blocks are registered. The octree was refined adaptively until bins of octree could be evenly distributed to processors. The assembler and solver were tested on a generic helicopter configuration in terms of load balance, scalability, and memory usage.

Flow Simulations for NASA CRM Wing-Body-Tail with Implicit Hole Cutting Method

2013 ◽  
Vol 378 ◽  
pp. 355-361
Author(s):  
Jia Xu ◽  
Kun Qu ◽  
Jin Sheng Cai
Keyword(s):  
Separation Bubble ◽  
Linear Trend ◽  
Grid Method ◽  
Smooth Transition ◽  
Overset Grid ◽  
Cutting Method ◽  
Flow Simulations ◽  
Overlapping Grids ◽  
Daunting Task ◽  
Overset Grid Method

The overset grid method eases the time of grid generation and provides great flexibility to handle topologically complex configurations, but the generation for a system of overlapping grids is an expensive and daunting task. Based on a hierarchical overset grid strategy, implicit holt cutting method developed to ensure grid connectivity within a framework suitable for multi-grid. Viscous flows around NASA CRM wing-body-tail configuration were simulated by an in-house CFD solver called Exstream. Compared with CFL3D and OVERFLOW, The results of Exstream show that: the smooth transition of surface pressure contour in the overlapping region indicates that the interpolation between the overlapping grids can offer sufficient accuracy, and it demonstrates the accuracy and efficiency of implicit holt cutting method and Exstream solver. The lift data matches well with those of CFL3D, OVERFLOW and Exstream and follows a nearly linear trend as angle of attack varies from 0.00 to 3.00 deg. In addition, there is a flow separation bubble near the trailing edge of wing-fuselage junction.

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