DU00-W-212 airfoil polars, laminar inflow
Description
Averaged lift and drag coeffficients of a DU00-W-212 profile in laminar flow (background turbulence level approx. 0.3%) at Reynolds numbers 500,000 and 900,000.
Data is obtained with a three-component load cell and via integration of 48 scanned pressure tabs along the chord.
Standard wind tunnel corrections according to Allen & Vincenti are applied.
Data sets 119, 120, 121, 122: flow tripped on the surface at 1.5% chord on upper airfoil side, 10% chord on lower airfoil side
Data sets 104, 107, 119, 122: measured starting at negative angles of attack (AOA) to positive AOAs
Data sets 105, 106, 120, 121: measured starting at positive angles of attack (AOA) to negative AOAs
The experiment was performed within in the EU-funded project AVATAR (www.eera-avatar.eu).
Files
104_DU00-W-212_laminar_Re500k_avg_WTc_loadcell.txt
Files
(2.6 MB)
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Additional details
References
- Heißelmann, H. et al.: Experimental airfoil characterization under tailored turbulent conditions. Journal of Physics: Conference Series 753 (2016) 072020; doi:10.1088/1742-6596/753/7/072020
- www.eera-avatar.eu