Actions for Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine I - Analysis of Turbine Performance

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Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine I - Analysis of Turbine Performance

Author
Golladay, Richard L.
Published
August 23, 1948.
Physical Description
1 electronic document
Additional Creators
Dietz, Robert O., Jr. and Conrad, Earl W.
Online Version

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
A wind tunnel investigation was conducted to determine the performance of a turbine operating as an integral part of a turbojet engine. Data was obtained while the engine was running over full operable range of speeds at various altitudes and flight mach numbers, and with four nozzles of different outlet areas.A maximum turbine efficiency of 0.875 was obtained at altitude of 15 thousand feet, Mach number 0.53, and corrected turbine speed of 5900 rpm.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 20030064096.
NACA-RM-E8A23.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15636667