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Flight-determined characteristics of an air intake system on an F-111A airplaneFlow phenomena of the F-111A air intake system were investigated over a large range of Mach number, altitude, and angle of attack. Boundary-layer variations are shown for the fuselage splitter plate and inlet entrance stations. Inlet performance is shown in terms of pressure recovery, airflow, mass-flow ratio, turbulence factor, distortion factor, and power spectral density. The fuselage boundary layer was found to be not completely removed from the upper portion of the splitter plate at all Mach numbers investigated. Inlet boundary-layer ingestion started at approximately Mach 1.6 near the translating spike and cone. Pressure-recovery distribution at the compressor face showed increasing distortion with increasing angle of attack and increasing Mach number. The time-averaged distortion-factor value approached 1300, which is near the distortion tolerance of the engine at Mach numbers above 2.1.
Document ID
19720011346
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Hughes, D. L. (NASA Flight Research Center Edwards, CA, United States)
Johnson, H. J. (NASA Flight Research Center Edwards, CA, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-6679
H-661
Accession Number
72N18996
Funding Number(s)
PROJECT: RTOP 125-15-14-00-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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