ADDITIONAL EXPERIMENTAL INFORMATION
2nd
AIAA CFD High Lift Prediction Workshop
Many experimental details can be found in the paper:
AIAA-2012-2924 by Rudnik et al.
The following provides some relevant highlights:
- The model is representative of a commercial wide-body
twin-jet high-lift configuration. It is denoted as DLR-F11. The configuration chosen for this workshop is the landing configuration,
with full-span flap (the slat is also full-span).
- The model was tested as a half model mounted on a
Peniche.
- The wing elements were un-tripped (no transition fixing).
- The configuration was tested in two wind tunnels:
- B-LSWT (low speed tunnel of Airbus-Deutchland in Bremen, Germany)
- Low Reynolds number (e.g., ReMAC = 1.35 x 106)
- "Freestream" velocity = 60 m/s
- Estimated* tunnel turbulence intensity Tu = 0.10 percent
(via verbal information from B-LSWT tunnel team member)
- Oil flow images, forces, moments, surface pressures,
and PIV data are available for HiLiftPW-2
- Tuft videos, surface IR-thermography, and hot-film were taken, but
are not available for HiLiftPW-2
- ETW (European Transonic Windtunnel in Cologne, Germany)
- High Reynolds number (e.g., ReMAC = 15.1 x 106)
- "Freestream" velocity = 37.5 m/s
- Estimated* tunnel turbulence intensity nominally Tu = 0.05 percent
(via unconfirmed web information:
click here)
- Forces, moments, and surface pressures are available
for HiLiftPW-2
- Tuft videos were taken, but are not available for HiLiftPW-2
* Tu levels are estimates, based on available information.
They are not guaranteed to be correct. Use with caution.
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Last Updated: 03/29/2013