Active control of self-excited roll oscillations of a rectangular flat plate wing with an aspect ratio of two was studied experimentally in a wind tunnel, using synthetic jet excitation near the leading edge. It was found that, by activating the synthetic jet excitation at an optimum frequency of St = 1, large amplitude roll oscillations could be attenuated and the onset of the oscillation can be delayed by up to Δαmax = 3.5° for extremely small values of momentum coefficient. High frame-rate Particle Image Velocimetry (PIV) measurements revealed a strong resonance between the synthetic jet excitation and shear layer instabilities. The resonance energizes the shear layer separated from the leading edge and results in a local flow field that is more typical of lower wing incidence, thus effectively suppressing roll oscillations.
Active Control of Self-Induced Roll Oscillations of a Wing Using Synthetic Jet
Tianxiang HuRelated information
1 Department of Mechanical Engineering, University of Bath, Bath, BA2 7AY, United Kingdom
, Zhijin WangRelated information2 Department of Mechanical Engineering, Member AIAA, University of Bath, Bath, BA2 7AY, United Kingdom
, Ismet GursulRelated information3 Department of Mechanical Engineering, Associate Fellow AIAA, University of Bath, Bath, BA2 7AY, United Kingdom
, Chris BowenRelated information1 Department of Mechanical Engineering, University of Bath, Bath, BA2 7AY, United Kingdom
Published Online: March 20, 2014
Abstract