Search

This contribution discusses the implementation of active flow-separation control for a three-dimensional high-lift wing-body configuration under atmospheric low-speed wind-tunnel conditions. The slot actuators are applied on the suction side of the trailing-edge flap to prevent local flow separation. The experimental results indicate that the pulsed blowing flow control technique is effective on the present configuration with a global performance enhancement. Numerical investigations are the focus of this article. The baseline case is characterized by substantial portions of separated flow. Thus, the influence of grid resolution and turbulence modeling is investigated. Based on this an intermediate mesh in combination with the Shear Stress Transport model gives the best compromise between quality and computational turnaround times. The steady Reynolds Averaged Navier Stokes (RANS) calculations carried out with constant blowing demonstrate the feasibility to simulate active flow control concepts. The key flow control method is the pulsed blowing. The verification of the unsteady RANS approach with active flow control shows that high computational resources are required for consistent numerical evaluations. The computational results highlight the ability of pulsed blowing at moderate blowing momentum coefficients to suppress the flow separation on the traillng-edge flap. The numerical results show an acceptable agreement with the experiments. [ABSTRACT FROM AUTHOR]