Transition locations on the LEISA high lift airfoil S.Reuß

A320 DDES on 2048 cores > Silvia Reuß, Dieter Schamborn > 30.04.2010

Transition locations on the LEISA high lift airfoilS.Reuß


Slide 2

Available experimental data

Two different settings were measured:

3eOptV1 which was measured in the slotted test section of the low speed wind tunnel NWB. From this measurement infra red pictures as well as pressure distributions are available.

3eOptV2 which was measured in the closed test section of the NWB. From this measurement pressure distributions as well as accoustical measurements are available.

All grids are for the OptV2 geometry, but the difference between those two is minimal:


Slide 3

Available experimental data

First we got the infrared measurement for the 3eOptV1 and the pressure distribution of the 3eOptV2 both for α=7° angle of attack. A comparison of the pressure distributions for the two different test sections (slotted/closed) revealed strong deviations (see next 3 slides)

After consultation with the experimentalists it was clear, that we needed a different angle of attack for comparison with the data from the slotted test section. The suggestion was to use the α=8° case. Also the suspicion arouse, that there might occur transition on the slat for this angle of attack.

Now that we received the infrared pictures for the other incidence angles, it is clear, that no transition should be found on the slat.

Since no evaluated data is available, we conclude by simple optical judgment, that the transition locations for the α= 7° and α=8° case do not change significantly


Slide 4

Available experimental dataPressure distribution slat

Pressure distributions• OptV2 (closed section)• OptV1 (slotted section)

• Data is measured in three sections


Slide 5

Available experimental dataPressure distribution wing




Slide 6

Available experimental dataPressure distribution flap



Here the influence of the wind tunnel side walls can be clearly seen. The curves with the most points are the measurements at the mid section


Slide 7

Flow

Available experimental dataIR slat and main wing upper side, α=7°


Slide 8

Available experimental dataIR slat and main wing upper side, α=8° Flow


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Available experimental dataIR wing and flap upper side, α=7° Flow


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Slide 19

New numerical resultsSpalart Allmaras Model A new grid was built with some modifications:

The farfield distance was increased to 100c

The resolution of the three element noses was reduced a bit

The resolution of the slat wake and above the flap was increased

The resulting grid has again about 200000 points per layer

Calculations with this new grid showed a clear difference compared to those on the old grid (2d/3d hybrid grid that can be found on the ATAAC site)

These differences are due to the small farfield distance! Calculations with farfield vortical correction show a clear trend towards the new results

New calculations use a critical N-factor of 7.18, where the theoretically expected value is in the range of 7.18 to 7.3. Originally this value should be calibrated using the experimentally given transition locations, but since all calculations showed earlier transition, this procedure was not successful.


Slide 20

Pressure distribution comparison old/new gridSA model


Slide 21

Pressure distribution new gridSA model

With the new grid a corrected angle of attack of α=5° is needed when the Spalar-Allmaras model is used

Even though the pressure distribution does not show the plateau on the flap the flow seperates


Slide 22

Skin friction new gridSA model

With the new grid a corrected angle of attack of α=5° is needed when the Spalar-Allmaras model is used

Even though the pressure distribution does not show the plateau on the flap the flow seperates


Slide 23

Convergence new gridSA model

The RANS calculations with the SA model converge, but slower as with the old grid, where about 40000 iterations were sufficient


Slide 24

Pressure distribution new gridSST model

With the new grid a corrected angle of attack of α=6° is needed when the Menter-SST model is used


Slide 25

Skin friction new gridSST model

With the new grid a corrected angle of attack of α=6° is needed when the Menter-SST model is used


Slide 26

Convergence new gridSST model

The RANS calculations with the SST model do not converge in steady calculations


Slide 27

Convergence new gridSST model

An unsteady restart from the steady solution yields a converged solution (time step is scaled for better presentability)


Slide 28

Transition locations on new grid

The black lines indicate the old suggested transition locations. With the new grid and Ncrit=7.18 the SA model yields transition on the slat.

4° and 5° transition lines coincide


Slide 29

New recommendations We recommend to use the new grid, to prevent wrong results because of the small

farfield distance (Can be found on the ATAAC site as hybrid_mandatory)

We recommend to use the SA model with a corrected angle of attack of α=5° and following transition locations:

We recommend to use the SST model with a corrected angle of attack of α=6° and following transition locations:

Since the SST model shows a much better agreement with the experimental data, DLR is considering to use SST based DES.

*) The transition location on the lower side of the wing did not converge completely, but is considered to have small influence. No experimental data is available for the lower side.

Slat Wing Flap

Upper side Laminar xtr=0.189 xtr=0.953

Lower side Laminar xtr=0.59-0.633* Laminar

Upper side Laminar xtr=0.1815 xtr=0.949

Lower side Laminar xtr=0.59-0.633* Laminar


Slide 30

Wiggles in Pressure distribution

At several point some wiggles in the pressure distribution could be observed. A close look to the surfaces built by centaur reveals the reason: The surface normals at some cells deviate noticeably from the neighboring ones

I do not have an idea how to prevent centaur from producing such bad cells

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Transition locations on the LEISA high lift airfoil S.Reuß