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An experimental study of the nonlinear dynamic phenomenon known as wing rockAn experimental investigation into the physical phenomena associated with limit cycle wing rock on slender delta wings has been conducted. The model used was a slender flat plate delta wing with 80-deg leading edge sweep. The investigation concentrated on three main areas: motion characteristics obtained from time history plots, static and dynamic flow visualization of vortex position, and static and dynamic flow visualization of vortex breakdown. The flow visualization studies are correlated with model motion to determine the relationship between vortex position and vortex breakdown with the dynamic rolling moments. Dynamic roll moment coefficient curves reveal rate-dependent hysteresis, which drives the motion. Vortex position correlated with time and model motion show a time lag in the normal position of the upward moving wing vortex. This time lag may be the mechanism responsible for the hysteresis. Vortex breakdown is shown to have a damping effect on the motion.
Document ID
19900058097
Document Type
Conference Paper
Authors
Arena, A. S., Jr. (Notre Dame Univ. IN, United States)
Nelson, R. C. (Notre Dame, University IN, United States)
Schiff, L. B. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
AIRCRAFT STABILITY AND CONTROL
Report/Patent Number
AIAA PAPER 90-2812
Meeting Information
AIAA Atmospheric Flight Mechanics Conference(Portland, OR)
Funding Number(s)
CONTRACT_GRANT: NCA2-406
Distribution Limits
Public
Copyright
Other