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A comprehensive plan for helicopter drag reductionCurrent helicopters have parasite drag levels 6 to 10 times as great as fixed wing aircraft. The commensurate poor cruise efficiency results in a substantial degradation of potential mission capability. The paper traces the origins of helicopter drag and shows that the problem (primarily due to bluff body flow separation) can be solved by the adoption of a comprehensive research and development plan. This plan, known as the Fuselage Design Methodology, comprises both nonaerodynamic and aerodynamic aspects. The aerodynamics are discussed in detail and experimental and analytical programs are described which will lead to a solution of the bluff body problem. Some recent results of work conducted at the Naval Ship Research and Development Center (NSRDC) are presented to illustrate these programs. It is concluded that a 75-per cent reduction of helicopter drag is possible by the full implementation of the Fuselage Design Methodology.
Document ID
19750054284
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Williams, R. M.
Montana, P. S.
(U.S. Naval National Command, Ship Research and Development Center Bethesda, Md., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1975
Subject Category
Aircraft Design, Testing And Performance
Meeting Information
Meeting: National Symposium on Helicopter Aerodynamic Efficiency
Location: Hartford, CN
Start Date: March 6, 1975
End Date: March 7, 1975
Accession Number
75A38356
Distribution Limits
Public
Copyright
Other

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