Experimental investigation of axial-flow compressor inlet stage operating at transonic relative inlet Mach numbers : blade-coordinate data

George W. Lewis, Jr.
naca-rm-e52c27
Jun 1952


Supplementary blade-design data including rotor- and stator-blade coordinates and mean-line angles at the leading and the trailing edges are presented for a transonic axial-flow compressor inlet stage.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1952/naca-rm-e52c27.pdf