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Multigrid Algorithm for Computing Hypersonic, Chemically Reacting Flows

Cited 3 time in Web of Science Cited 10 time in Scopus
Authors
Kim, Sung-soo; Kim, Chongam; Rho, Oh-Hyun
Issue Date
2001
Publisher
American Institute of Aeronautics and Astronautics
Citation
Journal of Spacecraft and Rockets, vol. 39, no.3, 2002, pp. 439-446
Abstract
A robust and efficient multigrid method for computing inviscid and viscous high-speed steady-state reactive flows is presented. Curve-fitted data are used to calculate equilibrium properties. Nonequilibrium flows are calculated using five-species and two-temperature air models. The advection upstream splitting method by pressure-based weight functions is used to acquire robustness and spatial accuracy in capturing a shock and resolving a boundary layer. The five-stage Runge– Kutta and lower-upper symmetric Gauss– Seidel schemes are adopted for efficient time integration. The chemical source terms are treated in a point-implicit manner when five-stage Runge– Kutta is used. To overcome the stability problem in applying the multigrid method to high-speed reactive flow calculations, a modified damped prolongation and a new implicit residual smoothing are proposed. The proposed methods are applied to the computations of hypersonic equilibrium and nonequilibrium flows over a half-cylinder. The results reveal the robustness of the proposed methods and substantial multigrid speed-ups in both the equilibrium and nonequilibrium test cases.
ISSN
0022-4650
Language
English
URI
http://hdl.handle.net/10371/6932
DOI
https://doi.org/10.2514/2.3776
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College of Engineering/Engineering Practice School (공과대학/대학원)Dept. of Mechanical Aerospace Engineering (기계항공공학부)Journal Papers (저널논문_기계항공공학부)
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