A discrete-vortex model for the arbitrary motion of a thin airfoil with fluidic control
A low-order model for the arbitrary motion of a thin airfoil with trailing edge fluidic control is derived from basic fluid mechanics principles. The model consist of solving a single ordinary differential equation with a special treatment of a vortex shedding criteria. The model is compared with experimental and high-order numerical simulations and the results give a reasonable means of predicting the lift and moment on a thin airfoil. Furthermore, the model is extended to account for the actuation and control due to the synthetic jet actuation near the trailing edge. The model response is compared to experimental results.
© 2011 Elsevier Ltd. Received 15 October 2010; Revised 23 February 2011; accepted 26 February 2011. Available online 21 March 2011. The authors kindly acknowledge the insight gained from the experimental and computational results of D. P. Brzozowski, A. Glezer, A. T. Kutay, J. A. Muse, A. J. Calise, O. Lopez, and R .D. Moser. This research was funded by the Air Force Office of Scientific Research, grant no. FA9550-05-1-0411.