Analysis of two-spool turboprop-engine characteristics

Elmer H. Davison
naca-rm-e57c21
Jun 1957


Two-spool turboprop engines with an over-all compressor pressure ratio of 12 split 6-2, 3-4, and 2-6 between the outer and inner compressors were analytically investigated for a range of turbine-inlet temperatures and flight conditions.

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