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Transonic aeroelasticity analysis for rotor bladesA numerical method is presented for calculating the unsteady transonic rotor flow with aeroelasticity effects. The blade structural dynamic equations based on beam theory were formulated by FEM and were solved in the time domain, instead of the frequency domain. For different combinations of precone, droop, and pitch, the correlations are very good in the first three flapping modes and the first twisting mode. However, the predicted frequencies are too high for the first lagging mode at high rotational speeds. This new structure code has been coupled into a transonic rotor flow code, TFAR2, to demonstrate the capability of treating elastic blades in transonic rotor flow calculations. The flow fields for a model-scale rotor in both hover and forward flight are calculated. Results show that the blade elasticity significantly affects the flow characteristics in forward flight.
Document ID
19890060298
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chow, Chuen-Yen
(Colorado, University Boulder, United States)
Chang, I-Chung
(NASA Ames Research Center Moffett Field, CA, United States)
Gea, Lie-Mine
(Colorado Univ. Boulder, CO, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Structural Mechanics
Report/Patent Number
AIAA PAPER 89-2212
Meeting Information
Meeting: AIAA Applied Aerodynamics Conference
Location: Seattle, WA
Country: United States
Start Date: July 31, 1989
End Date: August 2, 1989
Sponsors: AIAA
Accession Number
89A47669
Funding Number(s)
CONTRACT_GRANT: NCC2-508
Distribution Limits
Public
Copyright
Other

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