NDLI: Performance optimization of helicopter rotor blades

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Performance optimization of helicopter rotor blades

Content Provider	NASA Technical Reports Server (NTRS)
Author	Walsh, Joanne L.
Copyright Year	1991
Description	As part of a center-wide activity at NASA Langley Research Center to develop multidisciplinary design procedures by accounting for discipline interactions, a performance design optimization procedure is developed. The procedure optimizes the aerodynamic performance of rotor blades by selecting the point of taper initiation, root chord, taper ratio, and maximum twist which minimize hover horsepower while not degrading forward flight performance. The procedure uses HOVT (a strip theory momentum analysis) to compute the horse power required for hover and the comprehensive helicopter analysis program CAMRAD to compute the horsepower required for forward flight and maneuver. The optimization algorithm consists of the general purpose optimization program CONMIN and approximate analyses. Sensitivity analyses consisting of derivatives of the objective function and constraints are carried out by forward finite differences. The procedure is applied to a test problem which is an analytical model of a wind tunnel model of a utility rotor blade.
File Size	1049088
Page Count	24
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19910016823
Archival Resource Key	ark:/13960/t27993008
Language	English
Publisher Date	1991-04-01
Access Restriction	Open
Subject Keyword	Aircraft Design, Testing And Performance Helicopters Momentum Design Analysis Hovering Optimization Rotary Wings Horizontal Flight Degradation Tapering Flight Characteristics Algorithms Horsepower Wind Tunnel Tests Mathematical Models Wind Tunnel Models Aerodynamic Characteristics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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