Wind tunnel cl, cd data for Re=2.000.000 incl. AOA=0? -- CFD Online Discussion Forums

February 9, 2016, 10:21	Wind tunnel cl, cd data for Re=2.000.000 incl. AOA=0?	#1
klausb Senior Member Klaus Join Date: Mar 2009 Posts: 250 Rep Power: 22	Hello, to complete an evaluation, I am looking for wind tunnel lift (cl) and drag (cd) data for a common airfoil (NACA0015, NACA0012, ClarkY...) at (or close to) a reynolds number of 2x10⁶ and including angle-of-attack (AOA) of 0 degrees. Any idea, where I could find such information? Klaus

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