Incipient torsional stall flutter aerodynamic experiments on a swept three-dimensional wingThe aerodynamics of small amplitude pitching motions near stall have been studied experimentally in order to improve understanding of the torsional stall flutter problem for propeller blades. A model wing was oscillated in pitch at several small amplitudes over a wide and representative range of conditions. Unsteady surface pressures were measured and integrated to determine the aerodynamic damping at five spanwise stations. Strong negative damping was found for motions centered near static stall for all studied reduced frequencies, Mach numbers, and sweep angles. The 30-deg sweptback configuration was found to become negatively damped over the entire span nearly simultaneously, while the unswept model exhibited local regions of negative damping that moved toward the wing tip as the mean angle of attack was increased.
Document ID
19910047382
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lorber, Peter F. (United Technologies Research Center East Hartford, CT, United States)
Carta, Franklin O. (United Technologies Research Center East Hartford, CT, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 91-0935
Meeting Information
Meeting: AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference