Forschung im HLRN-Verbund 2011

147Figure 1: Top figure shows the identification of longitudinal vortices using vorticity criteria colored by normalizedu-velocity component due to leading edge perturbation. Two bottom figures show the effect of stall suppressiondue to leading edge flow control in comparison with the baseline flow producing leading edgetype stall at an angle of attack of 9.5 ◦ .More Information1. KROLL, N., ROSSOW, C.-C., SCHWAMBORN,D., BECKER, K., HELLER, G.:MEGAFLOW -A Numerical Flow Simulation Tool for TransportAircraft Design. ICAS Congress 2002, Toronto,09.-13.09.2002, ICAS, CD-Rom, S. 1.105.1-1.105.20, 2002.2. SCHWAMBORN, D., GERHOLD, T., HEINRICH,R.:The DLR TAU-Code: Recent Applicationsin Research and Industry. In: P. Wesseling,E. Oate, J. Priaux (Eds), ECCOMAS CFD,Egmond aan Zee, The Netherlands, 2006.3. MENTER, F.R.:Zonal two-equation k-ω turbulencemodels for aerodynamic flows. AIAA Paper,AIAA − 93 − 2906 (1993).4. MAHMOOD, S.; RADESPIEL, R.:RANS simulationof jet actuation in a boundary layer flowusing Chimera grids. Deutscher Luft- undRaumfahrtkongress, 08 − 10 September 2009,Aachen, Germany.5. PETER SCHOLZ, SAQIB S. MAHMOOD, MAR-CUS CASPER, ROLF RADESPIEL:Experimentaland Numerical Investigations on the control ofAirfoil Stall using Vortex Generator Jets. AIAA2010-4250, 5th Flow Control Conference 28June - 1 July 2010, Chicago, Illinois.FundingEuropean Union LEBox-JTI-CS-SFWA-01-003(CLEANSKY), Joint Technical Initiative forAeronautics and Air TransportIngenieurwissenschaften