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Wake integration for three-dimensional flowfield computations: Theoretical development

Abstract:

This paper examines the analytical, experimental, and computational aspects of the determination of the drag acting on an aircraft in flight, with or without powered engines, for subsonic/transonic flow. Using a momentum balance approach, the drag is represented by an integral over a crossflow plane at an arbitrary distance behind the aircraft. Asymptotic evaluation of the integral shows the drag can be decomposed into three components corresponding to streamwise vorticity and variations in e...

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Publication status:
Published

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Publisher copy:
10.2514/2.2465

Authors


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Institution:
University of Oxford
Department:
Oxford, MPLS, Mathematical Inst
Cummings, RM More by this author
Journal:
JOURNAL OF AIRCRAFT
Volume:
36
Issue:
2
Pages:
357-365
Publication date:
1999
DOI:
EISSN:
1533-3868
ISSN:
0021-8669
URN:
uuid:7cc0dee6-4d4c-4c75-95cd-a8d20dcdbb7a
Source identifiers:
15745
Local pid:
pubs:15745
Language:
English

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