XFOIL Version 6.96 Calculated polar for: NREL's S820 Airfoil 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 -0.1757 0.09134 0.08806 -0.0961 0.9618 0.0435 -11.250 -0.1779 0.08555 0.08227 -0.1003 0.9595 0.0447 -11.000 -0.1910 0.07794 0.07467 -0.1060 0.9558 0.0456 -10.750 -0.2047 0.07107 0.06775 -0.1106 0.9511 0.0456 -10.500 -0.2241 0.06458 0.06118 -0.1150 0.9469 0.0457 -10.250 -0.2415 0.05951 0.05603 -0.1172 0.9413 0.0457 -10.000 -0.2606 0.05533 0.05174 -0.1184 0.9344 0.0457 -9.750 -0.2842 0.05209 0.04834 -0.1183 0.9275 0.0459 -9.500 -0.3033 0.04958 0.04569 -0.1169 0.9195 0.0460 -9.250 -0.3295 0.04833 0.04425 -0.1131 0.9107 0.0463 -9.000 -0.3470 0.04742 0.04310 -0.1091 0.9036 0.0467 -6.000 -0.2622 0.02944 0.02205 -0.0906 0.8630 0.0337 -5.750 -0.2273 0.02658 0.01883 -0.0903 0.8612 0.0248 -5.500 -0.1937 0.02439 0.01645 -0.0905 0.8596 0.0225 -5.250 -0.1621 0.02297 0.01489 -0.0905 0.8581 0.0213 -5.000 -0.1472 0.02244 0.01437 -0.0885 0.8533 0.0215 -4.750 -0.1300 0.02179 0.01371 -0.0868 0.8498 0.0218 -4.500 -0.1122 0.02118 0.01308 -0.0853 0.8470 0.0237 -4.250 -0.0931 0.02058 0.01243 -0.0840 0.8446 0.0275 -4.000 -0.0894 0.02035 0.01220 -0.0804 0.8394 0.0296 -3.750 -0.0790 0.02010 0.01190 -0.0778 0.8351 0.0327 -3.500 -0.0615 0.01957 0.01126 -0.0762 0.8324 0.0402 -3.250 -0.0699 0.01667 0.01014 -0.0718 0.8295 0.4386 -3.000 -0.0832 0.01846 0.01282 -0.0626 0.8216 0.6818 -2.750 -0.0672 0.02077 0.01531 -0.0566 0.8190 0.7268 -2.500 -0.0442 0.02253 0.01714 -0.0519 0.8174 0.7487 -2.250 -0.0152 0.02219 0.01660 -0.0532 0.8159 0.7546 -2.000 -0.0123 0.02269 0.01708 -0.0495 0.8099 0.7572 -1.750 -0.0014 0.02302 0.01734 -0.0471 0.8053 0.7598 -1.500 0.0257 0.02298 0.01719 -0.0475 0.8033 0.7626 -1.250 0.0580 0.02278 0.01687 -0.0489 0.8019 0.7653 -1.000 0.0925 0.02251 0.01648 -0.0510 0.8007 0.7689 -0.750 0.0660 0.02376 0.01776 -0.0429 0.7906 0.7724 -0.500 0.0981 0.02369 0.01763 -0.0441 0.7888 0.7743 -0.250 0.1304 0.02364 0.01751 -0.0453 0.7875 0.7767 0.000 0.1138 0.02467 0.01853 -0.0391 0.7788 0.7815 0.250 0.1384 0.02480 0.01859 -0.0395 0.7756 0.7846 0.500 0.1705 0.02474 0.01850 -0.0406 0.7739 0.7864 0.750 0.2066 0.02463 0.01837 -0.0422 0.7727 0.7885 1.000 0.2442 0.02452 0.01822 -0.0441 0.7718 0.7911 1.250 0.2843 0.02432 0.01800 -0.0466 0.7710 0.7937 1.500 0.2590 0.02573 0.01939 -0.0394 0.7591 0.7989 1.750 0.2955 0.02554 0.01922 -0.0410 0.7579 0.8008 2.000 0.3348 0.02531 0.01900 -0.0430 0.7570 0.8030 2.250 0.3767 0.02505 0.01876 -0.0455 0.7563 0.8057 2.500 0.3566 0.02642 0.02014 -0.0390 0.7441 0.8112 2.750 0.3978 0.02606 0.01980 -0.0414 0.7430 0.8141 3.000 0.4405 0.02560 0.01939 -0.0437 0.7422 0.8162 3.250 0.4848 0.02513 0.01896 -0.0464 0.7414 0.8187 3.500 0.4723 0.02621 0.02007 -0.0407 0.7291 0.8239 3.750 0.4761 0.02706 0.02094 -0.0379 0.7191 0.8287 4.000 0.5166 0.02635 0.02034 -0.0394 0.7168 0.8316 4.250 0.5677 0.02511 0.01918 -0.0424 0.7158 0.8345 4.500 0.6315 0.02350 0.01766 -0.0473 0.7155 0.8371 4.750 0.6934 0.02185 0.01608 -0.0521 0.7146 0.8398 5.000 0.7061 0.02192 0.01623 -0.0497 0.7052 0.8444 5.250 0.7581 0.02052 0.01494 -0.0528 0.7024 0.8471 5.500 0.8135 0.01905 0.01355 -0.0566 0.6996 0.8500 5.750 0.8307 0.01883 0.01345 -0.0547 0.6896 0.8557 6.000 0.8835 0.01741 0.01210 -0.0581 0.6845 0.8590 6.250 0.8960 0.01722 0.01206 -0.0552 0.6735 0.8644 6.500 0.9190 0.01674 0.01169 -0.0541 0.6624 0.8703 6.750 0.9406 0.01620 0.01129 -0.0525 0.6501 0.8755 7.000 0.9573 0.01579 0.01099 -0.0501 0.6348 0.8821 7.250 0.9734 0.01538 0.01066 -0.0476 0.6160 0.8891 7.500 0.9791 0.01524 0.01059 -0.0433 0.5918 0.8986 7.750 0.9881 0.01512 0.01046 -0.0395 0.5558 0.9084 8.000 0.9934 0.01527 0.01033 -0.0353 0.4892 0.9203 8.250 0.9849 0.01616 0.01084 -0.0295 0.4236 0.9385 8.750 0.9805 0.01944 0.01344 -0.0241 0.2993 1.0000 9.000 0.9804 0.02122 0.01491 -0.0221 0.2531 1.0000 9.250 0.9838 0.02286 0.01632 -0.0204 0.2155 1.0000 9.500 0.9888 0.02443 0.01770 -0.0188 0.1863 1.0000 9.750 0.9959 0.02589 0.01902 -0.0174 0.1633 1.0000 10.000 1.0040 0.02729 0.02031 -0.0161 0.1445 1.0000 10.250 1.0130 0.02866 0.02162 -0.0148 0.1294 1.0000 10.500 1.0232 0.02997 0.02290 -0.0137 0.1163 1.0000 10.750 1.0338 0.03126 0.02419 -0.0126 0.1046 1.0000 11.000 1.0441 0.03260 0.02552 -0.0116 0.0939 1.0000 11.250 1.0536 0.03404 0.02694 -0.0105 0.0836 1.0000 11.500 1.0617 0.03560 0.02845 -0.0094 0.0740 1.0000 11.750 1.0722 0.03699 0.02992 -0.0085 0.0650 1.0000 12.000 1.0811 0.03859 0.03158 -0.0075 0.0570 1.0000 12.250 1.0874 0.04047 0.03342 -0.0063 0.0500 1.0000 12.500 1.0967 0.04207 0.03515 -0.0055 0.0437 1.0000 12.750 1.1033 0.04411 0.03722 -0.0043 0.0386 1.0000 13.000 1.1113 0.04591 0.03911 -0.0036 0.0342 1.0000 13.250 1.1175 0.04810 0.04132 -0.0026 0.0304 1.0000 13.500 1.1243 0.05006 0.04344 -0.0019 0.0270 1.0000 13.750 1.1281 0.05247 0.04584 -0.0012 0.0240 1.0000 14.000 1.1334 0.05486 0.04844 -0.0005 0.0215 1.0000 14.250 1.1364 0.05725 0.05093 -0.0002 0.0194 1.0000 14.500 1.1360 0.06034 0.05403 0.0003 0.0171 1.0000 14.750 1.1382 0.06320 0.05714 0.0006 0.0159 1.0000 15.000 1.1389 0.06629 0.06043 0.0008 0.0148 1.0000 15.250 1.1367 0.06963 0.06386 0.0007 0.0134 1.0000 15.500 1.1366 0.07305 0.06741 0.0007 0.0130 1.0000 16.000 1.1174 0.08296 0.07785 -0.0002 0.0121 1.0000 16.250 1.1085 0.08783 0.08296 -0.0014 0.0120 1.0000 16.500 1.0953 0.09349 0.08888 -0.0033 0.0117 1.0000 16.750 1.0817 0.09951 0.09514 -0.0058 0.0112 1.0000 17.000 1.0642 0.10666 0.10254 -0.0087 0.0117 1.0000 17.250 1.0484 0.11373 0.10983 -0.0123 0.0117 1.0000 17.500 1.0312 0.12143 0.11772 -0.0164 0.0119 1.0000 17.750 1.0125 0.13002 0.12651 -0.0217 0.0119 1.0000 18.000 0.9913 0.13964 0.13631 -0.0276 0.0121 1.0000 18.250 0.9723 0.14946 0.14629 -0.0341 0.0121 1.0000 18.500 0.9632 0.15655 0.15345 -0.0383 0.0126 1.0000