Altitude-wind-tunnel investigation of a 3000-pound-thrust axial-flow turbojet engine:II. Analysis of compressor performance

Dietz, Robert O., Berdysz, Joseph J., Howard, Ephraim M.
naca-rm-e8a26a
1948


Performance data for two compressors operating as an integral part of a turbojet engine were obtained for the full operable range of engine speeds at various simulated altitudes and flight Mach numbers. Performance characteristics for original and modified compressors are presented and the performance of the two compressors is compared. The relation of Raynolds number to the effects of altitude and flight Mach number on the compressor characteristics is discussed.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1948/naca-rm-e8a26a.pdf