Effects of coflow-jet active flow control on airfoil stall

Purpose Active flow control on the NACA 0024 airfoil defined as suction-injection jet at chord-based Reynolds number of 1.5 × 1e + 5 is studied. Design/methodology/approach The three-dimensional incompressible unsteady Reynolds-averaged Navier–Stokes equations with SST k- ω turbulence model are used to study effects coflow-jet (CFJ) dynamic and static stall phenomena. CFJ implementation conducted several momentum coefficients investigate their turnover. Furthermore, current work intends analyze performance by varying coefficient comparing all states baseline airfoil, which has not been studied in prior research investigations. Findings It observed that ( Cµ ) 0.06, lift low attack angles (up a = 15) dramatically increase. given lowered frequency 0.15 explored. In instance 0.07, curve does show noticeable feature compared 0.05, suggesting more powerful stronger can entirely stall. Originality/value