A new approach to the solution of boundary value problems involving complex configurationsA new approach for solving certain types of boundary value problems about complex configurations is presented. Numerical algorithms from such diverse fields as finite elements, preconditioned Krylov subspace methods, discrete Fourier analysis, and integral equations are combined to take advantage of the memory, speed and architecture of current and emerging supercomputers. Although the approach has application to many branches of computational physics, the present effort is concentrated in areas of Computational Fluid Dynamics (CFD) such as steady nonlinear aerodynamics, time harmonic unsteady aerodynamics, and aeroacoustics. The most significant attribute of the approach is that it can handle truly arbitrary boundary geometries and eliminates the difficult task of generating surface fitted grids.
Document ID
19870053956
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rubbert, P. E. (Boeing Military Airplane Development Seattle, WA, United States)
Bussoletti, J. E. (Boeing Military Airplane Development Seattle, WA, United States)
Johnson, F. T. (Boeing Military Airplane Development Seattle, WA, United States)
Sidwell, K. W. (Boeing Military Airplane Co. Seattle, WA, United States)
Rowe, W. S. (Boeing Military Airplane Development Seattle, WA, United States)
Samant, S. S. (Boeing Military Airplane Development Seattle, WA, United States)
Sengupta, G. (Boeing Military Airplane Development Seattle, WA, United States)
Weatherill, W. H. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Burkhart, R. H. (Boeing Computer Services Co. Seattle, WA, United States)
Woo, A. C. (NASA Ames Research Center Moffett Field, CA, United States)