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Aerodynamic and acoustic performance of a contracting cowl high throat Mach number inlet installed on NASA quiet engine CThe approach and takeoff performance was evaluated of a contracting cowl variable geometry design inlet installed on a high-bypass-ratio turbofan engine. The design was finalized after consideration of aerodynamic, acoustic, and mechanical factors which would lead to a viable flight worthy concept. The aerodynamic results are presented in terms of inlet recovery and distortion parameter as functions of throat Mach number, and acoustic results in terms of Perceived Noise Level. The contracting cowl high throat Mach number inlet is shown to be an attractive means to reduce forward radiated noise from a high bypass ratio turbofan engine.
Document ID
19760020080
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Blommer, H. E. (NASA Lewis Research Center Cleveland, OH, United States)
Schaefer, J. W. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1976
Subject Category
Aerodynamics
Report/Patent Number
E-8762
NASA-TM-X-73424
Meeting Information
Meeting: Aero-Acoustic Conf.
Location: Palo Alto, CA
Country: United States
Start Date: July 20, 1976
End Date: July 23, 1976
Sponsors: AIAA
Accession Number
76N27168
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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