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Application of slender wing benefits to military aircraftA review is provided of aerodynamic research conducted at the Langley Research Center with respect to the application of slender wing benefits in the design of high-speed military aircraft, taking into account the supersonic performance and leading-edge vortex flow associated with very highly sweptback wings. The beginning of the development of modern classical swept wing jet aircraft is related to the German Me 262 project during World War II. In the U.S., a theoretical study conducted by Jones (1945) pointed out the advantages of the sweptback wing concept. Developments with respect to variable sweep wings are discussed, taking into account early research in 1946, a joint program of the U.S. with the United Kingdom, the tactical aircraft concept, and the important part which the Langley variable-sweep research program played in the development of the F-111, F-14, and B-1. Attention is also given to hybrid wings, vortex flow theory development, and examples of flow design technology.
Document ID
19830068378
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Polhamus, E. C.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 11, 2013
Publication Date
October 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 83-2566
Accession Number
83A49596
Distribution Limits
Public
Copyright
Other

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