RANS Simulation and Experiments on the Stall Behaviour of an Airfoil with Laminar Separation Bubbles

A Fully Coupled Zonal RANS-LES Method for High Angle of Attack Flow

“…The smaller trailing-edge separation increases the lift coefficient slightly with respect to the pure LES reference computation as shown in Table 1. The comparison of the characteristic values of the pure LES computation, the experiments, and the RANS data 17 shows that the zonal RANS-LES method delivers more accurate results than the RANS. The drag coefficient resulting from the experiments is determined from pressure probe measurements on the surface.…”

“…The near stall flow phenomena of the HGR-01 research airfoil were studied at several angles of attack 17 . In this study, the configuration at an angle of attack of 12 o with a laminar separation bubble and trailingedge separation is simulated at a Reynolds number of Re c = 0.65 · 10 6 based on the chord length c. dients.…”

Differential Reynolds-Stress Modeling for Aeronautics

“…Experimental data [36] at a Mach number of M 0.073 and a Reynolds number of Re 0.6565 × 10 6 show a mixed stall behavior with both laminar leading-edge separations and turbulent separations from the trailing edge. However, up to about α 12 deg, the flow is dominated by a gradually growing trailing-edge separation, which therefore represents the focus of the investigation.…”

“…5 with 650 × 112 points in the structured near-wall part, which extends into the wake (c-topology) to accurately resolve the trailing-edge flow region. Mesh-refinement studies [36] applying a systematic variation of the cell sizes suggest virtually grid-independent results for the second-order spatial schemes used in the DLR TAU code. Both airfoil investigations (Secs.…”

“…Oil-flow visualization [36] shows the two-dimensional character of the trailing-edge separation up to α 12 deg; at higher angles of attack, growing three-dimensional structures occur.…”