Numerical Study of a NACA 0015 Circulation Control Aerofoil Using Synthetic Jets
Large eddy simulation of a NACA0015 circulation control aerofoil using synthetic jets is presented in this paper. In its usual appearance, the circulation control aerofoil features a rounded trailing edge (Coanda surface) which attracts an air jet provided upstream to modify the aerodynamic coefficients on the aerofoil. A chord Reynolds number of 1.10x10, excitation frequency of 175 Hz, momentum coefficients of 0.0044 to 0.0688, and angles of attack of 0deg, 6deg, and 12deg are employed in this study. Fluctuations in the lift and drag coefficients on the non actuated aerofoil are found to be governed by the vortex shedding frequency. Provided that the momentum coefficient is sufficiently high, the lift and drag coefficients tend to fluctuate at the synthetic jet frequency. The mean lift coefficient linearly increases with the momentum coefficient at a low momentum coefficient range and its incremental rate begins to decline at a high momentum coefficient range. Increasing the angle of attack of the aerofoil is observed to slightly reduce the slope of the lift increment.