James F. Dugan

发表

Effect of Various Blade Modifications on Performance of a 16-Stage High-pressure-ratio Axial-flow Compressor.Angles 3 deg, 1, Effect on Over-all Performance Characteristics of Decreasing Twelfth Through Fifteenth State Stator-blade Angles 3 deg

Arthur A. Medeiros, James E. Hatch, James F. Dugan, 1952 .

Effect of Design Variables on Performance of Mach 4.0 Hydrogen Expansion Engines

James F. Dugan, 1958 .

Prop-fan propulsion - Its status and potential

James F. Dugan, Bernard S. Gatzen, William M. Adamson, 1978 .

Matching Characteristics of J35-A-23 Compressor and Two-stage Turbine

James F. Dugan, Harold B. Finger, John J. Rebeske, 1951 .

Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics : effect of compressor interstage air bleed

James F. Dugan, John J. Rebeske, 1953 .

ANALYSIS OF STAGE MATCHING AND OFF-DESIGN PERFORMANCE OF MULTISTAGE AXIAL-FLOW COMPRESSORS

James F. Dugan, Harold B. Finger, 1952 .

Effect of Design Compressor Pressure Ratio on Performance of Hypothetical Two-Spool Nuclear-Powered Turbojet Engines

James F. Dugan, 1955 .

The NASA high-speed turboprop program

Brent A. Miller, James F. Dugan, Edwin J. Graber, 1980 .