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Helicopter rotor blade aerodynamic optimization by mathematical programmingFormal mathematical programing was applied to the aerodynamic rotor blade design process. The approach is to couple hover and forward flight analysis programs with the general-purpose optimization program CONMIN to determine the blade taper ratio, percent taper, twist distribution, and solidity which minimize the horsepower required at hover while meeting constraints on forward flight performance. Designs obtained using this approach for the blade of a representative Army helicopter compare well with those obtained using a conventional approach involving personnel-intensive parametric studies. Results from the present method can be obtained in 2 days as compared to 5 weeks required by the conventional procedure. Also the systematic manipulation of the design variables by the optimization procedure minimizes the need for the researcher to have a vast body of past experience and data in determining the influence of a design change on the performance.
Document ID
19870002320
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Walsh, J. L.
(NASA Langley Research Center Hampton, VA, United States)
Bingham, G. J.
(NASA Langley Research Center Hampton, VA, United States)
Riley, M. F.
(Kentron International, Inc. Hampton, Va., United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1984
Publication Information
Publication: Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2
Subject Category
Aircraft Design, Testing And Performance
Accession Number
87N11753
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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