병렬화된 비정렬 내재적 기법을 이용한 진동하는 3차원 날개 주위의 비점성 유동 계산Calculation of Inviscid Flows over an Oscillating 3-D Wing Using an Unstructured Implicit Parallel Solver

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Three-dimensional computations are performed for steady and unsteady transonic flows over a F-5 wing using a parallel implicit solver. The numerical scheme is based on a cell-centered finite-volume method with implicit Gauss-Seidel time integration and Roe`s flux-difference splitting. For parallel computation, local sub-domains are decomposed using MeTis library considering the balance of the number of cells. Parallel implementation is made using MPI library. Steady computation of a F-5 wing is performed to validate the capability of parallel computation. A case of an oscillating F-5 wing is also compared with experimental data for the validation of time accurate computations.
Publisher
한국항공우주학회
Issue Date
2000-06
Language
Korean
Citation

한국항공우주학회지, v.28, no.4, pp.27 - 34

ISSN
1225-1348
URI
http://hdl.handle.net/10203/76135
Appears in Collection
AE-Journal Papers(저널논문)
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