Actions for Loads and Performance Data from a Wind-Tunnel Test of Generic Model Helicopter Rotor Blades

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Loads and Performance Data from a Wind-Tunnel Test of Generic Model Helicopter Rotor Blades

Author
Yeager, William T., Jr.
Published
November 2005.
Physical Description
1 electronic document
Additional Creators
Wilbur, Matthew L.
Online Version

Availability

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
An investigation was conducted in the NASA Langley Transonic Dynamics Tunnel to acquire data for use in assessing the ability of current and future comprehensive analyses to predict helicopter rotating-system and fixed-system vibratory loads. The investigation was conducted with a generic model helicopter rotor system using blades with rectangular planform, no built-in twist, uniform radial distribution of mass and stiffnesses, and a NACA 0012 airfoil section. Rotor performance data, as well as mean and vibratory components of blade bending and torsion moments, fixed-system forces and moments, and pitch link loads were obtained at advance ratios up to 0.35 for various combinations of rotor shaft angle-of-attack and collective pitch. The data are presented without analysis.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 20050245188.
L-19185.
ARL-TR-3675.
NASA/TP-2005-213937.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15962356