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Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine. II - Performance of Inlet Guide Vanes as Separate ComponentThe inlet wide vanes for the supersonic compressor of the XJ55-FF-1 engine were studied as a separate component in order to determine the performance prior to installation in the compressor test rig. Turning angles approached design values, and increased approximately to through the inlet Mach number range from 0.30 to choke. A sharp break in turning angle was experienced when the choke condition was reached. The total-pressure loss through the guide vanes was approximately 1 percent for the unchoked conditions and from 5 to 6 percent when choked.
Document ID
20090023712
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Graham, Robert C. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Tysl, Edward R. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
May 3, 1949
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-SE9E03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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