XFOIL Version 6.94 Calculated polar for: NREL S-809 WIND TURBINE AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.1445 0.01436 0.00757 -0.0427 0.6195 0.5441 0.500 0.2031 0.01442 0.00758 -0.0442 0.6178 0.5466 1.000 0.2608 0.01436 0.00763 -0.0454 0.6160 0.5486 1.500 0.3186 0.01445 0.00785 -0.0465 0.6137 0.5506 2.000 0.3767 0.01456 0.00804 -0.0476 0.6112 0.5529 2.500 0.4352 0.01463 0.00817 -0.0488 0.6086 0.5553 3.000 0.4943 0.01476 0.00831 -0.0501 0.6057 0.5580 3.500 0.5508 0.01484 0.00853 -0.0510 0.6015 0.5605 4.000 0.6091 0.01465 0.00846 -0.0519 0.5951 0.5626 4.500 0.6664 0.01446 0.00840 -0.0525 0.5868 0.5649 5.000 0.7253 0.01406 0.00803 -0.0532 0.5766 0.5675 5.500 0.7814 0.01346 0.00751 -0.0533 0.5618 0.5706 6.000 0.8360 0.01289 0.00705 -0.0532 0.5451 0.5732 6.500 0.8882 0.01237 0.00676 -0.0526 0.5205 0.5756 7.000 0.9241 0.01255 0.00661 -0.0492 0.4094 0.5780 7.500 0.9246 0.01507 0.00834 -0.0411 0.2562 0.5807 8.000 0.9189 0.01711 0.00990 -0.0321 0.1646 0.5834 8.500 0.9188 0.01943 0.01191 -0.0253 0.1046 0.5858 9.000 0.9170 0.02238 0.01468 -0.0202 0.0585 0.5880 10.000 0.9294 0.02923 0.02144 -0.0146 0.0212 0.5933 10.500 0.9444 0.03233 0.02462 -0.0130 0.0187 0.5965 11.000 0.9610 0.03536 0.02776 -0.0116 0.0174 0.5995 11.500 0.9701 0.03902 0.03153 -0.0100 0.0164 0.6023 12.000 0.9842 0.04242 0.03510 -0.0089 0.0157 0.6053 12.500 0.9982 0.04600 0.03880 -0.0079 0.0149 0.6087 13.000 1.0134 0.04961 0.04248 -0.0073 0.0141 0.6121 13.500 1.0281 0.05329 0.04627 -0.0063 0.0137 0.6156 14.000 1.0475 0.05682 0.05000 -0.0058 0.0132 0.6199 14.500 1.0674 0.06046 0.05383 -0.0054 0.0129 0.6242 15.000 1.0861 0.06433 0.05797 -0.0051 0.0127 0.6283 15.500 1.1012 0.06886 0.06276 -0.0052 0.0124 0.6329 16.000 1.1115 0.07416 0.06832 -0.0057 0.0121 0.6378 16.500 1.1124 0.08093 0.07551 -0.0068 0.0122 0.6422 17.000 1.1045 0.08915 0.08411 -0.0091 0.0121 0.6472 17.500 1.1048 0.09631 0.09145 -0.0118 0.0117 0.6529 18.000 1.0668 0.11042 0.10616 -0.0182 0.0120 0.6562 18.500 1.0262 0.12641 0.12264 -0.0271 0.0121 0.6594 19.000 0.9686 0.14802 0.14474 -0.0409 0.0125 0.6606 19.500 0.9041 0.17470 0.17175 -0.0585 0.0134 0.6595