1. Mandatory settings for hybrid RANS/LES computations on the LEISA high-lift 3-element airfoil (Preliminary version)

2. Test case set-up for hybrid RANS/LES
In general, AoA=6 and SST local transition for all 3 elements
For partner using SA based DES methods:
AoA =6, and SA local transition on slat and wing, full turb. on flap
Option: AoA=6, and SST transition for all 3 elements
New run 18% retracted chord length and 128 cells in spanwise direction
According to the mandatory grid (100c farfield distance, ~ points per layer): total number of points ~25Mio
Time step Δt=1e-5

3. Expected results Partners should provide Cd and Cl time history
Surface data: Cp, Cf (mean and r.m.s.)
Field data: mean values for velocity <ui>, velocity gradients d<ui>/dxj, pressure <p>, eddy viscosity; correlations of velocity fluctuations <ui’uj’> and r.m.s. pressure <p’-<p>>. Here <> denotes averaging in time and spanwise direction
Time series of pressure p(.,t) at single probes in the nose region of the main wing element for comparison with KULITE measurement. The positions of the KULITES will be comunicated as soon as they are available
DLR will check position of PIV windows in experiments. But data postprocessing is independent of this information

4. Assessment of resolved and modelled part of turbulent shear stress
Consider relative contribution of modelled to resolved shear stress
Actual DES modus
τxz-modelled
τxz-resolved
RANS simulation
100% 0%
(D)DES simulation
100% in RANS mode
0% in RANS mode
~50% „grey area“ ~50%
<10% in LES mode
> 90% in LES mode