The Parallel Implementation and Accuracy of Matrix Compression in the Method of Moments Code EIGER.
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Solution to n-body space mechanics problems via numerical integration - ibm 7090 - fortran program
A numerical procedure was developed to compute the inviscid super/hypersonic flow field about complex vehicle geometries accurately and efficiently. A second-order accurate finite difference scheme is used to integrate the three-dimensional Euler equations in regions of continuous flow, while all shock waves are computed as discontinuities via the Rankine-Hugoniot jump conditions. Conformal mappings are used to develop a computational grid. The effects of blunt nose entropy layers are computed in detail. Real gas effects for equilibrium air are included using curve fits of Mollier charts. Typical calculated results for shuttle orbiter, hypersonic transport, and supersonic aircraft configurations are included to demonstrate the usefulness of this tool.
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Overview of the development of a CRAB/MELCOR workflow for mechanistic source term analysis