DU00-W-212 airfoil polars, sinusoidal inflow

Averaged lift and drag coeffficients of a DU00-W-212 profile in sinusoidally varying inflow (turbulence level approx. 5%) generated with an active grid 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 182, 183, 186, 188: flow tripped on the surface at 1.5% chord on upper airfoil side, 10% chord on lower airfoil side Data sets 183, 188, 242, 245: measured starting at positive angles of attack (AOA) to negative AOAs Data sets 182, 186, 243, 244: measured starting at negative angles of attack (AOA) to positive AOAs The experiment was performed within in the EU-funded project AVATAR (www.eera-avatar.eu).