Application of finite element code Q3DFLO-81 to turbomachinery flow fields
Schulz, H. D.
Shreeve, R. P.
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Through-flow and blade-to-blade calculations were made in association with a number of experimental research activities at the Turbopropulsion Laboratory, Naval Postgraduate School. The Q3DFL0-81 code was operated on an IBM 370-3033 mainframe computer. The flow through a single stage axial research compressor was computed and compared with both probe survey and stage performance map measurments. Swirling flow produced by a vaned out-flow generator for a radial diffuser test facility was calculated for both large low-speed and small-scale high-speed versions of the device. Flow through a two-dimensional compressor cascade of "controlled-dif fusion" blade shapes was calculated and the results compared with experimental data, and with predictions obtained using the NASA code QSONIC.
NPS Report NumberNPS67-84-005
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