NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Dynamic-stall and structural-modeling effects on helicopter blade stability with experimental correlationThe effects of blade and root-flexure elasticity and dynamic stall on the stability of hingeless rotor blades are investigated. The dynamic stall description is based on the ONERA models of lift, drag, and pitching moment. The structural analysis is based on three blade models that range from a rigid flap-lag model to two elastic flap-lag-torsion models, which differ in representing root-flexure elasticity. The predictions are correlated with the measured lag damping of an experimental isolated three-blade rotor; the correlation covers rotor operations from near-zero-thrust conditions in hover to highly stalled, high-thrust conditions in foward flight. That correlation shows sensitivity of lag-damping predictions to structural refinements in blade and root-flexure modeling. Moreover, this sensitivity increases with increasing control pitch angle and advance ratio. For high-advance-ratio and high-thrust conditions, inclusion of dynamic stall generally improves the correlation.
Document ID
19950056095
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Barwey, D.
(Washington Univ. St. Louis, MO, United States)
Gaonkar, Gopal H.
(Florida Atlantic Univ. Boca Raton, FL, United States)
Date Acquired
August 16, 2013
Publication Date
April 1, 1994
Publication Information
Publication: AIAA Journal
Volume: 32
Issue: 4
ISSN: 0001-1452
Subject Category
Structural Mechanics
Accession Number
95A87694
Funding Number(s)
CONTRACT_GRANT: DAAL-03-91-G-0007
CONTRACT_GRANT: NAG2-797
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available