Control of Flow Separation using Fluidic Oscillators on a NACA 0015 Aerofoil

In this study, the use of fluidic oscillators as a separation control device has been explored. A 2D wing having cross-section NACA 0015 embedded with a span-wise array of oscillators was tested in a wind tunnel. Hot-wire anemometry was used to characterize the oscillators. Surface pressure measurements and oil flow visualizations were carried out to measure the performance of oscillators. From pressure measurements, it was found that actuated wing stalled at a higher angle compared to the un-actuated wing. Actuated momentum produced up to 80% increase in lift coefficient and up to 6◦ increments in the stall angle. Oil flow visualizations provided an insight into the separation control mechanism of oscillators and also showed that a spacing of 10 times the nozzle width was the most effective.