An aeroelastic analysis with a generalized dynamic wakeAn aeroelastic model with generalized dynamic wake is developed for application in the integration of aerodynamic, dynamic, and structural optimization of a rotor blade. The investigation is carried out with special attention to efficiency and accuracy of aeroelastic modeling. Each blade is assumed to be an elastic beam undergoing flap bending, lead-lag bending, elastic twist and axial deflections. The nonuniform blade is discretized into finite beam elements, each of which consists of twelve degrees of freedom. Such important blade design variables as pretwist, and chordwise offsets of the blade center of gravity and of the aerodynamic center from the elastic axis have been included in the analysis. Aerodynamic loads are computed from unsteady blade element theory where the rotor three-dimensional unsteady wake is modeled using a generalized dynamic wake theory. The noncirculatory loads based on unsteady thin airfoil theory are also included.
Document ID
19920064308
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
He, Cheng J. (NASA Langley Research Center Hampton, VA, United States)
Peters, David A. (Georgia Institute of Technology Atlanta, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Subject Category
Aircraft Design, Testing And Performance
Meeting Information
Meeting: AHS International Specialists'' Meeting on Rotorcraft Basic Research