DU00-W-212 airfoil polars, sinusoidal inflow

<p>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&nbsp;and 900,000.</p> <p>Data is obtained with a three-component load cell and via integration of 48 scanned pressure tabs along the chord.<br> Standard wind tunnel corrections according to Allen &amp; Vincenti are applied.</p> <p>Data sets 182, 183,&nbsp;186, 188:&nbsp;flow tripped on the surface at 1.5% chord on upper airfoil side, 10% chord&nbsp;on lower airfoil side<br> Data sets 183,&nbsp;188, 242, 245:&nbsp;measured starting at positive angles of attack (AOA) to negative AOAs<br> Data sets 182,&nbsp;186, 243, 244:&nbsp;measured starting at negative angles of attack (AOA) to positive AOAs</p> <p>The experiment was performed within in the EU-funded project AVATAR (www.eera-avatar.eu).</p>