An advanced fan stage
Designed to meet the requirements for the first stage of a two-stage-to-orbit hypersonic vehicle. The fan stage was designed by GE engineers following their standard design practice, with close collaboration from NASA engineers.
This compressor map serves as the basis for Figures 1, 3, and 4 in GPPS-TC-2026-0083.
About this fan
This was a 57% scale research fan tested in the NASA compressor rig. It had the following design parameters:
Reference:
Kenneth L. Suder, Patricia S. Prahst, Scott A. Thorp
Results Of An Advanced Fan Stage Operating Over A Wide Range Of Speed & Bypass Ratio – Part I: Fan Stage Design And Experimental Results
ASME GT2010-22825
Figures showing the measured data and the smooth map
Tables for use with performance programs
The map tables are available in two variants:
Note that the file extension must be changed to MAP after downloading if you want to use the map with GasTurb.
Additional figures from my experimental map smoothing program
