Flow Simulations by Enhanced Implicit-Hole-Cutting Method on Overset Grids

Jia Xu; Jinsheng Cai; Qiuhong Liu; Kun Qu

doi:10.2514/1.c032283

Flow Simulations by Enhanced Implicit-Hole-Cutting Method on Overset Grids

Journal of Aircraft ◽

10.2514/1.c032283 ◽

2014 ◽

Vol 51 (5) ◽

pp. 1401-1409 ◽

Cited By ~ 11

Author(s):

Jia Xu ◽

Jinsheng Cai ◽

Qiuhong Liu ◽

Kun Qu

Keyword(s):

Cutting Method ◽

Overset Grids ◽

Flow Simulations

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Three-dimensional viscous flow simulations over the VLS using overset grids

Journal of the Brazilian Society of Mechanical Sciences and Engineering ◽

10.1590/s1678-58782004000400009 ◽

2004 ◽

Vol 26 (4) ◽

Cited By ~ 1

Author(s):

E. Basso ◽

J. L. F. Azevedo

Keyword(s):

Viscous Flow ◽

Three Dimensional ◽

Overset Grids ◽

Flow Simulations

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

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.378.355 ◽

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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