DU00-W-212 airfoil polars, laminar inflow

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).