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An Experimental Investigation of NACA Submerged-Duct EntrancesThe results of a preliminary investigation of submerged duct entrances are presented. It is shown that an entrance of this type possess desirable critical speed and pressure recovery characteristics when used on a fuselage or nacelle in a region of low incremental velocity and thin boundary layer. The data obtained indicate that submerged entrances are most suitable for use with internal-flow systems which diffuse the air only a small amount: for example, those used with jet motors which have axial-flow compressors. Where complete diffusion of the air is required, fuselage-nose or wing leading edge inlets may prove to be superior. The results of the investigation have been prepared in such a form as to permit their use by a designer and the application of these data to a specific design is discussed.
Document ID
20050061115
Document Type
Other
Authors
Frick, Charles W. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Davis, Wallace F. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Randall, Lauros M. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Mossman, Emmet A. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Date Acquired
September 7, 2013
Publication Date
October 1, 1945
Subject Category
Aircraft Design, Testing and Performance
Report/Patent Number
NACA-ACR-5I20
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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