XFOIL Version 6.96 Calculated polar for: NREL's S817 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 -0.1535 0.09311 0.08873 -0.0940 0.7834 0.0179 -11.000 -0.1542 0.08859 0.08423 -0.0960 0.7820 0.0179 -10.750 -0.1539 0.08434 0.07999 -0.0980 0.7806 0.0179 -10.500 -0.1563 0.07946 0.07511 -0.1004 0.7793 0.0179 -10.250 -0.1562 0.07451 0.07015 -0.0997 0.7780 0.0127 -10.000 -0.1575 0.07066 0.06630 -0.1011 0.7767 0.0123 -9.750 -0.1667 0.06529 0.06093 -0.1042 0.7754 0.0120 -9.500 -0.2329 0.06996 0.06530 -0.1129 0.7789 0.0123 -9.250 -0.2432 0.06673 0.06202 -0.1131 0.7768 0.0120 -9.000 -0.2561 0.06355 0.05877 -0.1125 0.7748 0.0116 -8.750 -0.2423 0.04587 0.04115 -0.1065 0.7695 0.0094 -8.500 -0.2924 0.05559 0.05042 -0.1062 0.7710 0.0092 -8.250 -0.2965 0.05312 0.04786 -0.1042 0.7690 0.0091 -8.000 -0.2976 0.05039 0.04497 -0.1020 0.7669 0.0091 -7.750 -0.2958 0.04784 0.04227 -0.0999 0.7649 0.0090 -7.500 -0.2929 0.04468 0.03887 -0.0974 0.7631 0.0090 -7.250 -0.2868 0.04110 0.03497 -0.0948 0.7616 0.0092 -6.750 -0.2647 0.03770 0.03124 -0.0920 0.7589 0.0104 -6.500 -0.2496 0.03562 0.02889 -0.0905 0.7578 0.0115 -6.250 -0.2336 0.03284 0.02576 -0.0887 0.7566 0.0118 -6.000 -0.2155 0.03011 0.02270 -0.0870 0.7553 0.0119 -5.750 -0.1945 0.02761 0.01987 -0.0858 0.7539 0.0118 -5.500 -0.1697 0.02528 0.01718 -0.0850 0.7526 0.0118 -5.250 -0.1416 0.02332 0.01491 -0.0848 0.7513 0.0119 -5.000 -0.1112 0.02162 0.01295 -0.0850 0.7500 0.0124 -4.750 -0.0825 0.02045 0.01159 -0.0851 0.7487 0.0130 -4.500 -0.0582 0.01944 0.01056 -0.0847 0.7475 0.0139 -4.250 -0.0362 0.01887 0.00996 -0.0839 0.7464 0.0157 -4.000 -0.0153 0.01837 0.00940 -0.0830 0.7454 0.0186 -3.750 0.0034 0.01786 0.00888 -0.0817 0.7444 0.0215 -3.500 0.0220 0.01740 0.00836 -0.0804 0.7434 0.0258 -3.250 0.0409 0.01703 0.00794 -0.0792 0.7425 0.0304 -3.000 0.0584 0.01672 0.00766 -0.0778 0.7410 0.0377 -2.750 0.0768 0.01644 0.00739 -0.0765 0.7394 0.0504 -2.500 0.0955 0.01615 0.00716 -0.0753 0.7377 0.0796 -2.250 0.1015 0.01502 0.00682 -0.0725 0.7361 0.2937 -2.000 0.1028 0.01422 0.00741 -0.0676 0.7346 0.6916 -1.750 0.1267 0.01475 0.00788 -0.0665 0.7335 0.7266 -1.500 0.1515 0.01524 0.00834 -0.0655 0.7324 0.7433 -1.250 0.1769 0.01562 0.00865 -0.0648 0.7314 0.7544 -1.000 0.2027 0.01597 0.00896 -0.0641 0.7304 0.7626 -0.750 0.2290 0.01612 0.00902 -0.0640 0.7295 0.7700 -0.500 0.2565 0.01613 0.00892 -0.0645 0.7286 0.7720 -0.250 0.2817 0.01622 0.00896 -0.0645 0.7275 0.7727 0.000 0.3043 0.01638 0.00912 -0.0641 0.7258 0.7735 0.250 0.3274 0.01653 0.00927 -0.0638 0.7241 0.7744 0.500 0.3512 0.01666 0.00938 -0.0637 0.7223 0.7754 0.750 0.3759 0.01678 0.00948 -0.0636 0.7207 0.7764 1.000 0.4011 0.01690 0.00959 -0.0637 0.7194 0.7775 1.250 0.4268 0.01702 0.00970 -0.0639 0.7182 0.7788 1.500 0.4532 0.01712 0.00979 -0.0641 0.7171 0.7802 1.750 0.4806 0.01720 0.00986 -0.0646 0.7160 0.7818 2.000 0.5087 0.01726 0.00991 -0.0652 0.7151 0.7833 2.250 0.5369 0.01735 0.01001 -0.0658 0.7143 0.7847 2.500 0.5536 0.01779 0.01051 -0.0646 0.7117 0.7864 2.750 0.5678 0.01827 0.01107 -0.0628 0.7083 0.7876 3.000 0.5881 0.01859 0.01145 -0.0621 0.7061 0.7889 3.250 0.6116 0.01880 0.01172 -0.0618 0.7043 0.7902 3.500 0.6376 0.01894 0.01193 -0.0620 0.7029 0.7915 3.750 0.6648 0.01906 0.01211 -0.0624 0.7017 0.7930 4.000 0.6933 0.01915 0.01225 -0.0630 0.7007 0.7945 4.250 0.7232 0.01921 0.01239 -0.0638 0.6997 0.7961 4.750 0.7349 0.02066 0.01404 -0.0577 0.6893 0.8014 5.000 0.7634 0.02068 0.01416 -0.0581 0.6878 0.8028 5.250 0.7962 0.02052 0.01412 -0.0593 0.6866 0.8042 5.500 0.7830 0.02154 0.01524 -0.0528 0.6773 0.8070 5.750 0.8736 0.01801 0.01173 -0.0616 0.6696 0.8070 6.000 0.8940 0.01711 0.01092 -0.0597 0.6555 0.8092 6.250 0.8966 0.01691 0.01080 -0.0550 0.6414 0.8122 6.500 0.8940 0.01723 0.01121 -0.0499 0.6281 0.8156 6.750 0.8850 0.01819 0.01230 -0.0444 0.6143 0.8185 7.000 0.8663 0.02015 0.01437 -0.0385 0.5966 0.8224 7.250 0.8892 0.01975 0.01402 -0.0376 0.5665 0.8253 7.500 0.9282 0.01780 0.01106 -0.0368 0.4207 0.8273 7.750 0.9101 0.01970 0.01262 -0.0309 0.3579 0.8316 8.000 0.8944 0.02174 0.01435 -0.0257 0.2973 0.8356 8.250 0.8841 0.02373 0.01603 -0.0217 0.2388 0.8399 8.500 0.8790 0.02558 0.01759 -0.0186 0.1844 0.8441 8.750 0.8797 0.02709 0.01892 -0.0160 0.1437 0.8477 9.000 0.8848 0.02841 0.02012 -0.0140 0.1141 0.8516 9.250 0.8929 0.02963 0.02126 -0.0125 0.0941 0.8561 9.500 0.9025 0.03079 0.02238 -0.0111 0.0790 0.8604 9.750 0.9131 0.03186 0.02350 -0.0098 0.0684 0.8650 10.000 0.9251 0.03290 0.02461 -0.0088 0.0611 0.8703 10.250 0.9351 0.03409 0.02582 -0.0075 0.0551 0.8761 10.500 0.9473 0.03510 0.02695 -0.0064 0.0502 0.8830 10.750 0.9579 0.03626 0.02816 -0.0053 0.0456 0.8908 11.000 0.9675 0.03749 0.02948 -0.0041 0.0426 0.9007 11.250 0.9790 0.03858 0.03075 -0.0029 0.0399 0.9135 11.500 0.9917 0.03970 0.03200 -0.0023 0.0369 0.9330 12.000 1.0146 0.04236 0.03483 -0.0013 0.0323 1.0000 12.250 1.0284 0.04363 0.03621 -0.0009 0.0300 1.0000 12.500 1.0412 0.04496 0.03762 -0.0005 0.0279 1.0000 12.750 1.0518 0.04653 0.03922 0.0001 0.0260 1.0000 13.000 1.0630 0.04809 0.04089 0.0007 0.0245 1.0000 13.250 1.0762 0.04947 0.04243 0.0011 0.0228 1.0000 13.500 1.0878 0.05100 0.04408 0.0015 0.0210 1.0000 13.750 1.0975 0.05270 0.04586 0.0018 0.0196 1.0000 14.000 1.1057 0.05463 0.04787 0.0022 0.0180 1.0000 14.250 1.1161 0.05635 0.04979 0.0026 0.0163 1.0000 14.500 1.1246 0.05820 0.05175 0.0026 0.0148 1.0000 14.750 1.1292 0.06047 0.05407 0.0027 0.0135 1.0000 15.000 1.1373 0.06254 0.05637 0.0029 0.0118 1.0000 15.250 1.1442 0.06468 0.05865 0.0028 0.0104 1.0000 15.500 1.1472 0.06730 0.06135 0.0026 0.0095 1.0000 15.750 1.1507 0.07008 0.06437 0.0027 0.0083 1.0000 16.000 1.1529 0.07298 0.06743 0.0025 0.0074 1.0000 16.250 1.1519 0.07637 0.07096 0.0021 0.0069 1.0000 16.500 1.1499 0.08001 0.07477 0.0015 0.0063 1.0000 16.750 1.1487 0.08364 0.07862 0.0008 0.0054 1.0000 17.000 1.1394 0.08858 0.08378 -0.0002 0.0054 1.0000 17.250 1.1376 0.09249 0.08781 -0.0016 0.0048 1.0000 17.500 1.1266 0.09805 0.09359 -0.0033 0.0049 1.0000 17.750 1.1174 0.10353 0.09924 -0.0056 0.0047 1.0000 18.000 1.1033 0.11013 0.10600 -0.0086 0.0044 1.0000 18.250 1.0931 0.11630 0.11239 -0.0117 0.0043 1.0000 18.500 1.0758 0.12419 0.12049 -0.0158 0.0042 1.0000 18.750 1.0578 0.13276 0.12927 -0.0207 0.0042 1.0000 19.000 1.0374 0.14238 0.13904 -0.0265 0.0044 1.0000