NREL's S806A Airfoil x/c y/c 1.00000 0.00000 0.97998 0.00677 0.95995 0.00940 0.93994 0.01206 0.91994 0.01484 0.90000 0.01795 0.85000 0.02791 0.80000 0.03813 0.75000 0.04853 0.70002 0.05874 0.65003 0.06795 0.60002 0.07532 0.55001 0.08058 0.50000 0.08372 0.45000 0.08496 0.40000 0.08464 0.35000 0.08293 0.29999 0.07985 0.24999 0.07535 0.19998 0.06924 0.14999 0.06120 0.11998 0.05520 0.09996 0.05055 0.07997 0.04524 0.06000 0.03905 0.04992 0.03548 0.03999 0.03154 0.02990 0.02695 0.01990 0.02161 0.00998 0.01470 0.00271 0.00691 0.00000 0.00000 0.00000 0.00021 0.00297 -0.00550 0.01002 -0.00889 0.01997 -0.01159 0.02998 -0.01377 0.03998 -0.01533 0.05000 -0.01659 0.05999 -0.01772 0.07999 -0.01965 0.10000 -0.02120 0.12000 -0.02252 0.15000 -0.02419 0.20000 -0.02634 0.25000 -0.02792 0.30000 -0.02903 0.35000 -0.02971 0.40000 -0.03000 0.45000 -0.02993 0.50000 -0.02949 0.55000 -0.02867 0.60000 -0.02745 0.65000 -0.02575 0.70001 -0.02340 0.75001 -0.02021 0.80000 -0.01621 0.85000 -0.01166 0.90000 -0.00686 0.91998 -0.00592 0.93998 -0.00540 0.95999 -0.00500 0.98000 -0.00462 1.00000 0.00000