Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine 1 - Performance Characteristics
Description:
A preliminary investigation of an axial-flow gas turbine-propeller engine was conducted. Performance data were obtained for engine speeds from 8000 to 13,000 rpm and altitudes from 5000 to 35,000 feet and compressor inlet ram pressure ratios from 1.00 to 1.17.
Date:
August 2, 1948
Creator:
Saari, Martin J. & Wallner, Lewis E.
Item Type:
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Partner:
UNT Libraries Government Documents Department