DU00-W-212 airfoil polars, laminar inflow
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https://zenodo.org/record/1098534
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资源简介：
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).
创建时间：
2024-08-02
