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Inlet design for high-speed propfansA two-part study was performed to design inlets for high-speed propfan installation. The first part was a parametric study to select promising inlet concepts. A wide range of inlet geometries was examined and evaluated - primarily on the basis of cruise thrust and fuel burn performance. Two inlet concepts were than chosen for more detailed design studies - one apropriate to offset engine/gearbox arrangements and the other to in-line arrangements. In the second part of this study, inlet design points were chosen to optimize the net installed thrust, and detailed design of the two inlet configurations was performed. An analytical methodology was developed to account for propfan slipstream effects, transonic flow efects, and three-dimensional geometry effects. Using this methodology, low drag cowls were designed for the two inlets.
Document ID
19830056739
Document Type
Reprint (Version printed in journal)
Authors
Little, B. H., Jr. (Lockheed-Georgia Co. Marietta, GA, United States)
Hinson, B. L. (Lockheed-Georgia Co. Marietta, GA, United States)
Date Acquired
August 11, 2013
Publication Date
October 1, 1982
Subject Category
AERODYNAMICS
Report/Patent Number
SAE PAPER 821359
Funding Number(s)
CONTRACT_GRANT: NAS3-22751
Distribution Limits
Public
Copyright
Other