NACA 8-Stage Compressor
This map of an eight stage axial compressor with a pressure ratio of 10 may be usefull for modeling older turbojets.
This compressor map serves as the basis for Figure 7 in GPPS-TC-2026-0083.
About this compressor
This compressor was designed for use as a research compressor and tested by NACA.
Design Point Data:
| Mass Flow [kg/s] | 32.3 |
| Pressure Ratio | 11 |
| Circumferential speed [m/s] | 371 |
| Rotational speed [rpm] | 13380 |
| Tip Diameter [m] | 0.38 |
| Radius Radio | 0.46 |
Figures of 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
