A 2D partially-parabolic procedure for axial-flow turbomachinery cascades

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dc.contributor.author A. K. Singhal en_US
dc.contributor.author D. Brian Spalding en_US
dc.date.accessioned 2014-10-21T15:51:31Z
dc.date.available 2014-10-21T15:51:31Z
dc.date.issued 1976 en_US
dc.identifier.other ARC/R&M-3807 en_US
dc.identifier.uri https://reports.aerade.cranfield.ac.uk/handle/1826.2/3087
dc.description.abstract A general finite-difference procedure is presented for the calculation of steady, two-dimensional 'partially-parabolic' flows, with special reference to turbine cascade problems. It can be used for incompressible, subsonic, supersonic or transonic flows. It can be characterised as an 'iterative space-marching' method. The method is more economical in computer storage than time-marching procedures; and computer time is also low. The main distinguishing features of the method are: (a) use of a streamline coordinate system, (b) one-dimensional storage for all variables except pressure, (c) solution by repeated marching integration from upstream to downstream. The capabilities of the method are demonstrated by application to six different inviscid-flow problems. In each case, computed results are compared with the available analytical or experimental data. Good agreement is shown. The method is capable of including momentum transfer across streamlines by viscous effects; it can easily incorporate a two-equation turbulence model; and heat transfer can be simultaneously calculated. en_US
dc.relation.ispartofseries Aeronautical Research Council Reports & Memoranda en_US
dc.title A 2D partially-parabolic procedure for axial-flow turbomachinery cascades en_US

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