Effects of CoFlow-Jet Active Flow Control on Airfoil Stall

Abstract Originality/value – Furthermore, the current work intends to analyze the CoFlow-Jet performance by varying the jet momentum coefficient and comparing all states to the baseline airfoil, which has not been studied in prior research investigations. Purpose – Active flow control on the NACA 0024 airfoil defined as suction-injection jet at the chord-based Reynolds number of 1.5×10 5 is studied. Design/methodology/approach – The three-dimensional incompressible unsteady Reynolds-averaged Navier-Stokes equations with the SST k- ω turbulence model are utilized to study the effects of CoFlow-Jet on the dynamic and static stall phenomena. CoFlow-Jet implementation is conducted with several momentum coefficients to investigate their turnover. Furthermore, the current work intends to analyze the CoFlow-Jet performance by varying the Reynolds number and jet momentum coefficient and comparing all states to the baseline airfoil, which has not been studied in prior research investigations. Findings – It is observed that at the momentum coefficient ( C μ ) of 0.06, the lift coefficients at low attack angles (up to α = 15°) dramatically increase. Furthermore, the dynamic stall at the given Reynolds number and with the lowered frequency of 0.15 is explored. In the instance of C μ = 0.07, the lift coefficient curve does not show a noticeable stall feature compared to C μ = 0.05, suggesting that a more powerful stronger jet can entirely control the dynamic stall.