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Automatic grid generation for complex geometries

Published online by Cambridge University Press:  04 July 2016

R. J. Smith  and
M. A. Leschziner
R. J. Smith
Affiliation:
Department of Mechanical Engineering , UMIST , Manchester, UK
M. A. Leschziner
Affiliation:
Department of Mechanical Engineering , UMIST , Manchester, UK
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Abstract

A novel automatic grid generation method for complex CFD applications has been developed, driven by the need of the industrial CFD practitioner to reduce the turnaround time from an initial CAD geometry to obtaining a flow simulation. The method uses a subdivision strategy, allowing hanging nodes in a Cartesian unstructured mesh environment and is combined with a non-overlapping, semi-structured surface grid. Unusually, the surface grid is the end rather than the starting point of the present approach. This reversal of gridding strategy allows usability to be enhanced, in that the grid generation is reduced to one automatic step. The capabilities of the method are demonstrated by reference to selected inviscid and viscous flow solutions using the Fluent code Rampant v4.0 as a flow solver.

Type
Research Article
Information
The Aeronautical Journal , Volume 100 , Issue 991 , January 1996 , pp. 7 - 14
Copyright
Copyright © Royal Aeronautical Society 1996 

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References

1. Weatherill, N.P. and Forsey, C.R. Grid generation and flow calculations for complex aircraft geometries using a multi-block scheme, AIAA Paper 84-1665, 1984.Google Scholar
2. Jameson, A., Baker, T.J. and Weatherill, N.P. Calculation of inviscid transonic flow over a complete aircraft, AIAA Paper 86-0103, January 1986.Google Scholar
3. Tysinger, T.L. and Caughey, D.A. Distributed parallel processing applied to an implicit multigrid Euler/Navier-Stokes algorithm, AIAA Paper 93-0057, 31st Aerospace Sciences Meeting and Exhibit, Reno, January 1993.Google Scholar
4. Purvis, J.W. and Burkhalter, J.E. Prediction of critical Mach number for store configurations, AIAA J, 1979, 17, (11), pp 1170–1177.Google Scholar
5. De Zeeuw, D. and Powell, K.G. An adaptively refined cartesian mesh solver for the Euler equations, J Comput Phys, 1993, 104, pp 56–68.Google Scholar
6. Coirier, W.J. An Adaptively-Refined, Cartesian, Cell-Based Scheme for the Euler and Navier-Stokes Equations, PhD Thesis, NASA TM 106754, 1994.Google Scholar
7. Karman, S.L. Jr SPLITFLOW: A 3D unstructured cartesian/prismatic grid CFD code for complex geometries, AIAA Paper 95-0343, 33rd Aerospace Sciences Meeting and Exhibit, Reno, January 1995.Google Scholar
8. Melton, J.E., Berger, M.J., Aftosmis, M.J. and Wong, M.D. 3D applications of a Cartesian grid Euler method, AIAA Paper 95-0853, 33rd Aerospace Sciences Meeting and Exhibit, Reno, January 1995.Google Scholar
9. Smith, R.J. and Johnston, L.J. An automatic method of computational grid generation and flow solution for complex geometries, AIAA Paper 95-0214, 33rd Aerospace Sciences Meeting and Exhibit, Reno, January 1995.Google Scholar
10. Bonet, J. and Peraire, J. An alternating digital tree (ADT) algorithm for 3D geometric searching and intersection problems, Int J Num Meth Eng, 1991, 31, pp 1–7.Google Scholar
11. Schneiders, R., Oberschelp, W., Weiler, F., Kopp, R., Bunten, R. and Franzke, M. Automatic generation of hexahedral element meshes for the simulation of metal forming processes, Proc 4th International Conference on Numerical Grid Generation in Computational Fluid Dynamics and Related Fields, Weatherill, N.P. et al (Eds), April 1994, pp 589–602.Google Scholar
12. Spragle, G., Smith, W.A. and Weiss, J.M. Hanging node solution adaption on unstructured grids, AIAA Paper 95-0214, 33rd Aerospace Sciences Meeting and Exhibit, Reno, January 1995.Google Scholar
13. Jones, J.P. and Launder, B.E. The prediction of laminarisation with a two-equation model of turbulence, Int J Heat and Mass Transfer, 1972, 15, p 301.Google Scholar
14. Cook, P.H., McDonald, M.A. and Firmin, M.C.P. Aerofoil RAE 2822 — pressure distributions, boundary layer and wake measurements, AGARD AR 138, A6-1-A6-77, May 1979.Google Scholar
15. Van Den Berg, B. and Gooden, J.H.M. Low-speed surface pressure and boundary layer measurement data for the NLR 7301 airfoil section with trailing edge flap, AGARD AR 303, A9-I-A9-I2, 1994.Google Scholar
16. Yakhot, V. and Orszag, S.A. Renormalisation group analysis of turbulence I: Basic theory, J Sci Comput, 1986, 1, (1), 1–51.Google Scholar
17. Stanewsky, E. and Thibert, J.J. Airfoil SKF 1.1 with maneuver flap, AGARD AR 138, A5-l-a5-29, May 1979.Google Scholar