Control of Laminar Separation Bubble over a NACA2415 Aerofoil at Low Re Transitional Flow Using Blowing/Suction | ||||
International Conference on Aerospace Sciences and Aviation Technology | ||||
Article 1, Volume 13, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT- 13, May 26 – 28, 2009, May 2009, Page 1-17 PDF (456.11 K) | ||||
Document Type: Original Article | ||||
DOI: 10.21608/asat.2009.23439 | ||||
View on SCiNiTO | ||||
Authors | ||||
M. Serdar GENÇ1, 2; Ünver KAYNAK3 | ||||
1Corresponding author+ | ||||
2Student, School of Civil Aviation, University of Erciyes, Kayseri, 38039, Turkey. | ||||
3Professor, Department of Mechanical Engineering, TOBB University of Economics and Technology, Ankara, 06560, Turkey. | ||||
Abstract | ||||
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. | ||||
Keywords | ||||
Laminar separation bubble; Flow separation control; Blowing; Suction; Transition models | ||||
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