New Approach to the 3-D Transonic Flow Analysis Using the STAR-106 Computer

Redhed, David D.; Chen, Allen W.; Hotovy, S.

doi:10.2514/3.61069

Cited by 10 publications

(5 citation statements)

References 4 publications

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“…In general, these attempts were successful and achieved an order of magnitude improvement in computing speed by enhancing the numerical stability. On the other hand, a class of computers designed for scientific computations; the CRAY-1, STAR 100, and ILLIAC IV became available (39)(40)(41)(42) . The most significant advance in computer hardware related to CFD at that time was the Cray's vector processor which permitted a vector to be processed at an exceptional high speed.…”

Section: The 1980smentioning

confidence: 99%

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Computational fluid dynamics application to aerospace science

Shang

2009

Aeronaut. j.

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critical stability criterion for finite-difference approximation and addressed the issue of resolving hydrodynamic shock as early as 1944 and his more accessible article in the literature was published six years later (2,3) . Under the similar war time security restriction, the spherical blast wave computation by G. I. Taylor was also delayed for public release until 1950 (4) . These pioneering works were performed to meet an urgent engineering need which set a pattern of science and technology development for practical applications.Harlow and his colleagues developed the particle in cell(PIC) method based on a combination Lagrangian-Eulerian description of the fluid motion (5) . The PIC method has showed how well suited it was to study time-dependent and multi-dimensional fluid motion. The effectiveness of this method is demonstrated through the applications to shock interaction, supersonic wakes, and hypersonic sharp leading-edge flows. This method is still in use today for Magneto-hydrodynamic research. At the same time, Hirt made a lasting contribution to turbulent transport properties simulation by highlighting the numerical challenges and providing guidance for future research (6) . All these accomplishments were accompanied by exhaustive proof in order to illustrate the validity of the approximations and the numerical accuracy. This rigorous process actually established the standards for all future CFD algorithm and numerical procedure research. The detailed derivation of formulations and extensive discussions on computational accuracy and limits of applicability became the accepted standard in CFD research. During that time, all valuable information was largely unknown to the aerospace science community. ABSTRACTA brief narration on significant accomplishments in computational fluid dynamics (CFD) for basic research and aerospace application is attempted to highlight the outstanding achievements by scientists and engineers of this discipline. To traverse such a vast domain, numerous and excellent contributions to CFD will be unintentionally overlooked by the author's limited exposure. Nevertheless it is an ardent hope that the present abridged literature review will aid to reaffirm excellence in research and to identify knowledge shortfalls both in aerodynamics and its modeling and simulation capability. The future modeling and simulation technology needs, as well as potential and fertile research areas, are humbly put forth for consideration.

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Section: The 1980smentioning

confidence: 99%

“…This option gave a new perspective, i.e., a drastic reduction in computing time. Several efforts on vectorisation of computer codes with varying degrees of success have been reported in the open literature (40,41) . The potential of increased speed in data processing rate is clear.…”

Section: The 1980smentioning

confidence: 99%

Computational fluid dynamics application to aerospace science

Shang

2009

Aeronaut. j.

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“…We should point out that ZEBRA I is not the same as the alternating line SOR scheme of Ref. 4, which solved alternating vertical lines in each / = constant cross-plane with vector instructions of length J/2 for each color. ZEBRA I has vector length 7x//2 for the </ > update, while the density and residual calculations can be volume vectorized.…”

Section: Zebra Imentioning

confidence: 99%

“…Obviously, a larger speed ratio would have been obtained using a finer mesh; the 64 x 28 x 20 mesh employed in Ref. 4 should be considered as a coarse 3-D mesh. Reference 4 rightly concluded that more study is needed to eliminate the short vector operations.…”

Section: Introductionmentioning

confidence: 99%

Vector Processor Algorithms for Transonic Flow Calculations

1980

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This paper discusses a number of algorithms for solving the transonic full-potential equation in conservative form on a vector computer, such as the CDC STAR-100 or the CRAY-1. Recent research with the "artificial density" method for transonics has led to development of some new iteration schemes which take advantage of vector-computer architecture without suffering significant loss of convergence rate. Several of these more promising schemes are described and two-and three-dimensional results are shown comparing the computational rates on the STAR and CRAY vector computers and the CYBER-175 serial computer. Schemes included are: 1) checkerboard SOR, 2) checkerboard leapfrog, 3) odd-even vertical line SOR, and 4) odd-even horizontal line SOR.

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“…Redhed, et al[1979] treated the three-dimensional small disturbance equation of transonic flow on the CDC STAR by using a red-black ordering of grid lines in the cross-flow plane and applying line SOR to all the red columns and then all the black5.5 ones. This yields a vector length of half the number of grid points in the cross-flow plane.…”

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confidence: 99%