Weekly Seminar: Spring 2013
Speaker: Dr. Xueying Deng (BUAA | Retired)
Title: "Active Control of Asymmetric Vortices-Induced Wing-Rock using Micro Tip Perturbation"
Date: Friday, February 15, 2013
Time: 11:00 a.m.
Location: Gilman Hall 50 (Marjorie M. Fisher Hall)
Wing-rock refers to an oscillating rotary motion of aircraft induced by asymmetric vortices over wing/body configurations during flight at high-angles-of-attack. Successful control of the wing-rock motion is critical in ensuring flight safety at the high-angles-of-attack regime. In this talk, I will describe an experimental investigation about a novel active control method that can effectively suppress or even eliminate the wing-rock motion using perturbations introduced by a micro bump installed near the nose tip of the wing/body configuration.
Free roll oscillation patterns of two wing/body configurations with low and high wing swept angles are investigated for angles of attack varying from low to high to document the effect of the perturbations from a micro bump located at a variety of circumferential locations near the nose tip. The results of the low swept wing model show that the wing rock motion patterns are strongly dependent on the circumferential position of the micro-perturbation near the nose tip of the model. Three types of free roll oscillation patterns are identified, including (a), the limit cycle wing rock at θ=0o or 180o, with θ being the circumferential angle of the micro-perturbation from the wind ward symmetric surface, (b), the irregular oscillation at θ=90o or 270o and (c), the tiny roll oscillation pattern for θ located at other circumferential positions. For the low swept wing model, a technique of suppressing wing rock by rotating the nose tip perturbation at frequencies higher than that of the free roll oscillation is introduced. It is shown that increasing the frequency of the rotating micro-perturbation significantly enhances the effect of suppression of the free wing-rock motion.
For the model with high swept wing, a different perturbation control technique is developed for suppression of the wing rock. This technique utilizes two pairs of asymmetric vortices, with one pair from the forebody and the other from the high swept wing, to control the wing rock. It is found that when the two pairs of asymmetric vortices are in phase, the wing rock appears to be stronger. However, when the two pair asymmetric vortices are in counter phase, achieved by adjusting the circumferential location of the micro perturbation at the nose tip, the amplitude of the wing rock is significantly reduced.
Prof. Xueying Deng is a leading aerodynamicist in China, with expertise in separated flow, vortex flow, shock wave/boundary layer interactions and free wing rock and its suppression. He received his bachelor’s degree in aerodynamics from Beijing University of Aeronautics and Astronautics in 1963 and has been a faculty member at the same university since his graduation, with full professorship awarded in 1986 and serving as vice president of the university from 1994 to 2000. From 1979 to 1982, he was a visiting scholar at the Department of Mechanical and Aerospace Engineering at Princeton University. He has won numerous awards for his outstanding achievements in aerodynamics research, including the prestigious National Science and Technology Award and the National Natural Science Award in China, and AIAA annual highlight for “the study of cylindrical and conical interactions between shock wave and boundary layer interactions” in 1984.
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