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.Prepared for: Naval Air Systems Command, Washington DChttp://archive.org/details/applicationoffin00schuN0001984WR 41099, N0001984WR 41134N
