XFOIL Version 6.96 Calculated polar for: NREL's S831 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 0.0919 0.09274 0.08800 -0.1668 0.8333 0.0219 -11.000 0.0953 0.08975 0.08501 -0.1679 0.8286 0.0223 -10.750 0.0989 0.08675 0.08199 -0.1691 0.8245 0.0226 -10.500 0.1017 0.08355 0.07875 -0.1706 0.8210 0.0228 -10.250 0.1027 0.08042 0.07565 -0.1717 0.8167 0.0230 -10.000 0.1035 0.07716 0.07240 -0.1731 0.8127 0.0232 -9.750 0.1025 0.07346 0.06869 -0.1748 0.8091 0.0231 -9.500 0.1003 0.06962 0.06483 -0.1770 0.8056 0.0229 -9.250 0.0927 0.06535 0.06059 -0.1795 0.8011 0.0229 -9.000 0.0813 0.06144 0.05664 -0.1813 0.7968 0.0226 -8.750 0.0682 0.05799 0.05310 -0.1821 0.7932 0.0224 -8.500 0.0341 0.05273 0.04765 -0.1800 0.7880 0.0148 -8.250 0.0232 0.05106 0.04594 -0.1777 0.7841 0.0145 -8.000 0.0191 0.04949 0.04428 -0.1764 0.7810 0.0165 -7.500 0.0058 0.04182 0.03603 -0.1707 0.7749 0.0112 -7.250 0.0090 0.03982 0.03388 -0.1688 0.7718 0.0111 -7.000 0.0158 0.03776 0.03165 -0.1672 0.7689 0.0109 -6.750 0.0256 0.03550 0.02914 -0.1657 0.7665 0.0107 -6.500 0.0389 0.03314 0.02649 -0.1645 0.7644 0.0105 -6.250 0.0518 0.03096 0.02405 -0.1628 0.7618 0.0103 -6.000 0.0654 0.02880 0.02161 -0.1609 0.7591 0.0101 -5.750 0.0826 0.02666 0.01916 -0.1594 0.7567 0.0100 -5.500 0.1032 0.02467 0.01685 -0.1582 0.7546 0.0099 -5.250 0.1264 0.02290 0.01477 -0.1573 0.7529 0.0100 -5.000 0.1510 0.02145 0.01307 -0.1567 0.7513 0.0103 -4.750 0.1756 0.02032 0.01175 -0.1561 0.7499 0.0107 -4.500 0.1955 0.01956 0.01087 -0.1549 0.7480 0.0111 -4.250 0.2111 0.01900 0.01030 -0.1530 0.7453 0.0118 -4.000 0.2297 0.01857 0.00985 -0.1518 0.7429 0.0126 -3.750 0.2509 0.01819 0.00942 -0.1511 0.7408 0.0159 -3.500 0.2743 0.01786 0.00905 -0.1509 0.7390 0.0195 -3.250 0.2989 0.01746 0.00862 -0.1509 0.7375 0.0263 -3.000 0.3249 0.01706 0.00821 -0.1514 0.7361 0.0369 -2.750 0.3527 0.01670 0.00779 -0.1521 0.7350 0.0499 -2.500 0.3718 0.01654 0.00764 -0.1511 0.7328 0.0643 -2.250 0.3917 0.01628 0.00752 -0.1504 0.7305 0.1045 -2.000 0.4105 0.01484 0.00778 -0.1507 0.7285 0.6207 -1.750 0.4342 0.01516 0.00807 -0.1499 0.7265 0.6532 -1.500 0.4592 0.01547 0.00832 -0.1493 0.7249 0.6728 -1.250 0.4851 0.01576 0.00855 -0.1488 0.7234 0.6874 -1.000 0.5117 0.01604 0.00876 -0.1486 0.7222 0.6996 -0.750 0.5406 0.01619 0.00882 -0.1490 0.7212 0.7064 -0.500 0.5699 0.01624 0.00876 -0.1500 0.7200 0.7091 -0.250 0.5841 0.01652 0.00904 -0.1479 0.7174 0.7114 0.000 0.6018 0.01677 0.00929 -0.1465 0.7151 0.7132 0.250 0.6229 0.01696 0.00947 -0.1457 0.7131 0.7152 0.500 0.6473 0.01709 0.00956 -0.1455 0.7114 0.7173 0.750 0.6741 0.01719 0.00961 -0.1459 0.7099 0.7195 1.000 0.7027 0.01727 0.00965 -0.1466 0.7086 0.7219 1.250 0.7329 0.01735 0.00967 -0.1477 0.7076 0.7244 1.500 0.7636 0.01743 0.00972 -0.1488 0.7067 0.7266 1.750 0.7919 0.01757 0.00985 -0.1494 0.7058 0.7285 2.000 0.7743 0.01848 0.01091 -0.1413 0.7008 0.7314 2.250 0.7863 0.01888 0.01134 -0.1389 0.6980 0.7342 2.500 0.8089 0.01912 0.01158 -0.1385 0.6963 0.7369 2.750 0.8351 0.01931 0.01177 -0.1389 0.6950 0.7397 3.000 0.8630 0.01946 0.01193 -0.1395 0.6939 0.7421 3.250 0.8919 0.01959 0.01210 -0.1402 0.6930 0.7440 3.500 0.9232 0.01966 0.01220 -0.1414 0.6922 0.7463 4.500 0.9013 0.02480 0.01764 -0.1217 0.6734 0.7597 4.750 0.9523 0.02390 0.01679 -0.1257 0.6753 0.7619 5.000 1.0025 0.02316 0.01609 -0.1298 0.6766 0.7644 6.500 1.0274 0.03021 0.02362 -0.1124 0.6476 0.7859 7.000 1.0403 0.03253 0.02615 -0.1078 0.6354 0.7924 7.250 1.0757 0.03181 0.02553 -0.1090 0.6348 0.7963 7.500 1.1161 0.03068 0.02450 -0.1107 0.6341 0.8006 8.000 1.1443 0.03110 0.02513 -0.1073 0.6194 0.8084 8.250 1.1368 0.03296 0.02708 -0.1034 0.6074 0.8130 8.750 1.1708 0.03324 0.02758 -0.1010 0.5909 0.8217 9.750 1.1878 0.03897 0.03375 -0.0924 0.5375 0.8431 10.000 1.2121 0.03866 0.03352 -0.0921 0.5214 0.8488 10.250 1.2631 0.03577 0.03060 -0.0937 0.4882 0.8557 10.500 1.2962 0.03406 0.02834 -0.0931 0.4144 0.8627 10.750 1.2864 0.03639 0.03038 -0.0893 0.3653 0.8707 11.000 1.2741 0.03916 0.03292 -0.0856 0.3221 0.8799 11.250 1.2637 0.04195 0.03552 -0.0824 0.2831 0.8914 11.500 1.2551 0.04461 0.03804 -0.0795 0.2471 0.9097 11.750 1.2476 0.04690 0.04023 -0.0767 0.2160 1.0000 12.000 1.2458 0.04953 0.04271 -0.0751 0.1843 1.0000 12.250 1.2463 0.05204 0.04508 -0.0738 0.1567 1.0000 12.500 1.2489 0.05440 0.04733 -0.0727 0.1329 1.0000 12.750 1.2528 0.05667 0.04952 -0.0717 0.1123 1.0000 13.000 1.2574 0.05892 0.05168 -0.0709 0.0943 1.0000 13.500 1.2686 0.06327 0.05596 -0.0694 0.0677 1.0000 13.750 1.2751 0.06543 0.05811 -0.0688 0.0568 1.0000 14.000 1.2819 0.06758 0.06030 -0.0683 0.0477 1.0000 14.250 1.2882 0.06979 0.06254 -0.0678 0.0398 1.0000 14.500 1.2935 0.07215 0.06492 -0.0673 0.0331 1.0000 14.750 1.2977 0.07466 0.06744 -0.0668 0.0276 1.0000 15.000 1.3035 0.07703 0.06988 -0.0664 0.0230 1.0000 15.250 1.3076 0.07964 0.07256 -0.0661 0.0193 1.0000 15.500 1.3115 0.08228 0.07524 -0.0658 0.0162 1.0000 15.750 1.3154 0.08499 0.07806 -0.0656 0.0138 1.0000 16.000 1.3183 0.08781 0.08094 -0.0654 0.0119 1.0000 16.250 1.3212 0.09070 0.08398 -0.0654 0.0101 1.0000 16.500 1.3236 0.09369 0.08708 -0.0654 0.0089 1.0000 16.750 1.3229 0.09715 0.09065 -0.0655 0.0080 1.0000 17.000 1.3242 0.10039 0.09405 -0.0657 0.0071 1.0000 17.250 1.3248 0.10372 0.09750 -0.0661 0.0065 1.0000 17.500 1.3226 0.10750 0.10137 -0.0666 0.0059 1.0000 17.750 1.3240 0.11081 0.10487 -0.0672 0.0052 1.0000 18.000 1.3245 0.11428 0.10848 -0.0680 0.0047 1.0000 18.250 1.3232 0.11806 0.11238 -0.0690 0.0043 1.0000 18.500 1.3185 0.12244 0.11690 -0.0702 0.0041 1.0000 18.750 1.3159 0.12654 0.12115 -0.0715 0.0040 1.0000 19.000 1.3127 0.13080 0.12560 -0.0730 0.0037 1.0000 19.250 1.3090 0.13517 0.13014 -0.0746 0.0036 1.0000