The analytical design and experimental test of a single-stage transoni
c axial-flow compressor are described. This design is the baseline of
a compressor design study in which several blade design parameters hav
e been systematically varied to determine their independent effects on
compressor performance. The baseline design consisted of ruggedizing
an existing compressor design that demonstrated outstanding aerodynami
c performance, to correct some undesirable aeromechanical characterist
ics. The design study was performed by varying only one design paramet
er at a time, keeping the other design variables as close as possible
to the baseline design. Specific design parameters of interest were th
ose for which very few data were available to determine their sensitiv
ity on compressor performance. This paper describes the baseline compr
essor design and its experimental performance. A detailed definition a
nd flow analysis of the baseline design test point (used as the basis
for all subsequent design variations) are provided.