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Preliminary noise tests of the engine-over-the-wing concept. 2: 10 deg - 20 deg flap positionPreliminary acoustic tests of the engine-over-the-wing concept as a method for reducing the aerodynamic noise created by conventional and short takeoff aircraft are discussed. Tests were conducted with a small wing section model having two flaps which can be set for either the landing or takeoff positions. Data was acquired with the flaps set at 10 degrees and 20 degrees for takeoff and 30 and 60 degrees for landing. The engine exhaust was simulated by an air jet from a convergent nozzle. Far field noise data are presented for nominal pressure ratios of 1.25, 1.4 and 1.7 for both the flyover and sideline modes.
Document ID
19720019380
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Reshotko, M. (NASA Lewis Research Center Cleveland, OH, United States)
Olsen, W. A. (NASA Lewis Research Center Cleveland, OH, United States)
Dorsch, R. G. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
June 1, 1972
Subject Category
Aircraft
Report/Patent Number
NASA-TM-X-68104
E-7038
Accession Number
72N27030
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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