Chiplight,
Thanks for the lead to the full article. It was an interesting report but its results are based on a computer simulation. With today's technology, it appears that the single flap (be it used as a Kaman trailing flap, or an aileron) can not provide a high enough amplitude (for collective and cyclic control) and at the same time a high enough frequency (for vibration elimination).
The Gurney flap is an interesting possibility, particularly since it's small size would allow for fast response rates. It appears that it works best when the airfoil is operating with trailing edge separation. The stalled tip of a retreating blade might benefit from the Gurney flap, as long as this flap did not impart a large moment about the pitch axis of the blade.
The 'rotor' is definitely the place for significant improvements in rotorcraft performance. Just providing separate root and tip controls (active blade twist with a frequency of 1/rev) will result in large benefits, such as much greater thrust, less vibration and lower noise. Then, the addition of a separate small amplitude but high frequency pitch change device should result in the proverbial jet-smooth ride.
The proposed leading and trailing edge tabs is a means of providing this small amplitude high frequency pitch change device. In addition, it should reduce 'the pitching and diving tendencies' mentioned by Lu.
Any critiques and comments are appreciated.