NREL's S805A Airfoil x/c y/c 1.00000 0.00000 0.98999 0.00155 0.97999 0.00344 0.97000 0.00551 0.95000 0.00984 0.93001 0.01414 0.90001 0.02014 0.85000 0.02918 0.80000 0.03779 0.75000 0.04626 0.70000 0.05461 0.65001 0.06273 0.60001 0.07048 0.55002 0.07756 0.50002 0.08340 0.45001 0.08732 0.40000 0.08893 0.35000 0.08831 0.30000 0.08579 0.24999 0.08144 0.19998 0.07514 0.14998 0.06657 0.11997 0.06007 0.09995 0.05500 0.07997 0.04920 0.05998 0.04241 0.04991 0.03849 0.03998 0.03416 0.02988 0.02914 0.01992 0.02331 0.00998 0.01581 0.00269 0.00731 0.00000 0.00000 0.00001 -0.00031 0.00296 -0.00619 0.00997 -0.01061 0.01994 -0.01432 0.02998 -0.01737 0.03995 -0.01976 0.05000 -0.02178 0.05998 -0.02359 0.07999 -0.02675 0.09999 -0.02942 0.11999 -0.03175 0.14999 -0.03475 0.19999 -0.03876 0.25000 -0.04180 0.30000 -0.04401 0.35000 -0.04547 0.40000 -0.04620 0.45000 -0.04600 0.50000 -0.04546 0.55000 -0.04384 0.60001 -0.04108 0.65001 -0.03696 0.70001 -0.03156 0.75000 -0.02519 0.80000 -0.01816 0.84999 -0.01111 0.89999 -0.00499 0.92999 -0.00212 0.95000 -0.00069 0.97000 0.00021 0.98000 0.00040 0.99000 0.00036 1.00000 0.00000