Document Type : Original Article
Student, School of Civil Aviation, University of Erciyes, Kayseri, 38039, Turkey.
Professor, Department of Mechanical Engineering, TOBB University of Economics and Technology, Ankara, 06560, Turkey.
In this study, control of flow over a NACA2415 aerofoil which experiences a laminar separation bubble at a transitional Reynolds number of 2x105 is computationally investigated using blowing or suction. In an earlier flow control study which involved the use of a leading edge slat, both the experimental and computational studies demonstrated significantly delayed stall angles. For these flows, employing the recently developed k-kL-ω and k-ω SST transition models were shown to accurately predict the location of the experimentally determined separation bubble. In the present case, a single jet with a width of 2.5% the chord length is placed on the aerofoil’s upper surface simulating the blowing/suction control at Re=2x105 and α = 8 degrees. Nearly 200 numerical simulations are carried out a range of parameters of jet locations, Ljet, jet velocity ratios, Rjet and jet angles, θjet are investigated. In the numerical results of blowing/suction, it is shown that the smaller blowing results are better larger blowing velocity ratios while the largest suction results are better
smaller suction velocity ratios independent of the suction jet locations.