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Formal optimization of hovering performance using free wake lifting surface theoryFree wake techniques for performance prediction and optimization of hovering rotor are discussed. The influence functions due to vortex ring, vortex cylinder, and source or vortex sheets are presented. The vortex core sizes of rotor wake vortices are calculated and their importance is discussed. Lifting body theory for finite thickness body is developed for pressure calculation, and hence performance prediction of hovering rotors. Numerical optimization technique based on free wake lifting line theory is presented and discussed. It is demonstrated that formal optimization can be used with the implicit and nonlinear objective or cost function such as the performance of hovering rotors as used in this report.
Document ID
19860019463
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Chung, S. Y. (Massachusetts Inst. of Tech. Cambridge, MA, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1986
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-CR-177103
NAS 1.26:177103
Accession Number
86N28935
Funding Number(s)
CONTRACT_GRANT: NAG2-275
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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