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Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, 3, Performance Characteristics with the High-Flow Compressor
A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-flow turbojet engine with a high flow compressor. Pressure altitudes included 5000 to 40000 feet with ram pressure ratios from 1.00 to 1.82. Altitudes included 20000 to 40000 feet and ram pressure ratios from 1.09 to 1.75. A comparison is made between engine performance with high flow and low flow compressors.
Date:
August 5, 1948
Creator:
Fleming, William A. & Golladay, Richard L.
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, 4 - Analysis of Compressor Performance
Operating characteristics of the 11-stage 4000-pound-thrust axial-flow turbojet engine were determined. A standard compressor and a compressor with the blade angles of the rotor and stator blades increased 5 degrees to obtain greater air flow, were investigated.
Date:
August 5, 1948
Creator:
Dietz, Robert O., Jr. & Suozzi, Frank L.
System:
The UNT Digital Library