XFOIL Version 6.96 Calculated polar for: EPPLER 266 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.000 -0.5510 0.06527 0.06171 -0.1052 0.6781 0.0060 -14.750 -0.5767 0.05733 0.05362 -0.1102 0.6750 0.0058 -14.500 -0.6048 0.05053 0.04662 -0.1135 0.6716 0.0058 -14.250 -0.6286 0.04547 0.04137 -0.1146 0.6683 0.0058 -14.000 -0.6422 0.04201 0.03775 -0.1145 0.6652 0.0059 -13.750 -0.6574 0.03876 0.03433 -0.1135 0.6617 0.0058 -13.500 -0.6614 0.03665 0.03207 -0.1124 0.6580 0.0059 -13.250 -0.6747 0.03387 0.02907 -0.1102 0.6543 0.0059 -13.000 -0.6743 0.03227 0.02735 -0.1086 0.6513 0.0060 -12.750 -0.6723 0.03080 0.02574 -0.1068 0.6481 0.0061 -12.500 -0.6742 0.02899 0.02377 -0.1045 0.6451 0.0061 -12.250 -0.6672 0.02794 0.02260 -0.1028 0.6422 0.0062 -12.000 -0.6628 0.02663 0.02115 -0.1007 0.6393 0.0062 -11.500 -0.6473 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-6.500 -0.3117 0.01309 0.00607 -0.0691 0.6013 0.0085 -6.250 -0.2889 0.01281 0.00577 -0.0684 0.6001 0.0087 -6.000 -0.2657 0.01256 0.00549 -0.0679 0.5989 0.0088 -5.750 -0.2442 0.01217 0.00507 -0.0669 0.5977 0.0091 -5.500 -0.2217 0.01186 0.00473 -0.0662 0.5963 0.0094 -5.250 -0.1982 0.01160 0.00446 -0.0656 0.5949 0.0097 -5.000 -0.1741 0.01138 0.00422 -0.0651 0.5936 0.0101 -4.750 -0.1498 0.01119 0.00400 -0.0647 0.5922 0.0105 -4.500 -0.1252 0.01100 0.00379 -0.0643 0.5910 0.0109 -4.250 -0.1003 0.01085 0.00361 -0.0640 0.5898 0.0113 -4.000 -0.0751 0.01070 0.00343 -0.0637 0.5884 0.0116 -3.750 -0.0498 0.01052 0.00325 -0.0634 0.5877 0.0125 -3.500 -0.0242 0.01036 0.00309 -0.0632 0.5868 0.0138 -3.250 0.0019 0.01023 0.00296 -0.0631 0.5858 0.0151 -2.750 0.0503 0.00969 0.00264 -0.0622 0.5835 0.0648 -2.500 0.0742 0.00941 0.00251 -0.0618 0.5824 0.1074 -2.250 0.0975 0.00908 0.00238 -0.0613 0.5814 0.1641 -1.750 0.1369 0.00797 0.00204 -0.0592 0.5791 0.3882 -1.500 0.1530 0.00720 0.00180 -0.0574 0.5779 0.5423 -1.250 0.1694 0.00662 0.00173 -0.0554 0.5766 0.6886 -1.000 0.1958 0.00663 0.00182 -0.0552 0.5754 0.7285 -0.750 0.2235 0.00670 0.00191 -0.0552 0.5742 0.7479 -0.500 0.2516 0.00679 0.00196 -0.0554 0.5728 0.7580 -0.250 0.2801 0.00686 0.00203 -0.0556 0.5719 0.7646 0.000 0.3087 0.00691 0.00207 -0.0559 0.5710 0.7701 0.250 0.3373 0.00695 0.00210 -0.0562 0.5699 0.7736 0.500 0.3660 0.00698 0.00214 -0.0565 0.5688 0.7759 0.750 0.3947 0.00701 0.00217 -0.0569 0.5676 0.7776 1.000 0.4234 0.00704 0.00218 -0.0573 0.5663 0.7789 1.250 0.4520 0.00707 0.00220 -0.0576 0.5650 0.7802 1.500 0.4805 0.00710 0.00222 -0.0580 0.5638 0.7815 1.750 0.5090 0.00713 0.00224 -0.0583 0.5623 0.7826 2.000 0.5373 0.00716 0.00227 -0.0587 0.5609 0.7837 2.250 0.5656 0.00721 0.00229 -0.0590 0.5595 0.7848 2.500 0.5937 0.00727 0.00233 -0.0593 0.5577 0.7860 2.750 0.6220 0.00730 0.00237 -0.0597 0.5562 0.7869 3.000 0.6503 0.00731 0.00240 -0.0600 0.5541 0.7878 3.250 0.6784 0.00732 0.00244 -0.0603 0.5515 0.7888 3.500 0.7062 0.00733 0.00247 -0.0605 0.5486 0.7897 3.750 0.7337 0.00737 0.00251 -0.0607 0.5458 0.7907 4.000 0.7607 0.00742 0.00256 -0.0608 0.5426 0.7916 4.250 0.7886 0.00745 0.00263 -0.0611 0.5397 0.7927 4.500 0.8163 0.00748 0.00269 -0.0613 0.5365 0.7938 4.750 0.8436 0.00752 0.00275 -0.0615 0.5328 0.7949 5.000 0.8699 0.00758 0.00281 -0.0614 0.5284 0.7960 5.250 0.8969 0.00762 0.00288 -0.0615 0.5231 0.7970 5.500 0.9233 0.00767 0.00295 -0.0615 0.5169 0.7981 5.750 0.9490 0.00775 0.00303 -0.0614 0.5106 0.7991 6.000 0.9747 0.00783 0.00312 -0.0612 0.5020 0.8002 6.250 0.9968 0.00798 0.00322 -0.0604 0.4844 0.8013 6.500 1.0167 0.00822 0.00339 -0.0592 0.4616 0.8023 6.750 1.0290 0.00870 0.00369 -0.0565 0.4251 0.8035 7.000 1.0392 0.00921 0.00406 -0.0535 0.3898 0.8051 7.250 1.0404 0.00982 0.00450 -0.0487 0.3514 0.8069 7.500 1.0446 0.01037 0.00494 -0.0445 0.3231 0.8085 7.750 1.0386 0.01124 0.00562 -0.0386 0.2824 0.8104 8.000 1.0391 0.01198 0.00623 -0.0342 0.2544 0.8122 8.250 1.0363 0.01286 0.00697 -0.0294 0.2247 0.8141 8.500 1.0321 0.01388 0.00786 -0.0247 0.1968 0.8160 8.750 1.0338 0.01481 0.00872 -0.0213 0.1775 0.8177 9.000 1.0324 0.01600 0.00982 -0.0178 0.1573 0.8194 9.250 1.0337 0.01721 0.01098 -0.0149 0.1408 0.8213 9.500 1.0367 0.01844 0.01219 -0.0125 0.1263 0.8232 9.750 1.0387 0.01984 0.01354 -0.0102 0.1103 0.8250 10.000 1.0382 0.02147 0.01510 -0.0079 0.0919 0.8268 10.250 1.0405 0.02299 0.01656 -0.0059 0.0779 0.8285 10.500 1.0437 0.02450 0.01803 -0.0042 0.0652 0.8302 10.750 1.0521 0.02573 0.01925 -0.0030 0.0583 0.8318 11.000 1.0527 0.02747 0.02092 -0.0012 0.0440 0.8334 11.250 1.0547 0.02917 0.02256 0.0004 0.0322 0.8349 11.500 1.0573 0.03085 0.02420 0.0018 0.0214 0.8363 11.750 1.0585 0.03268 0.02599 0.0033 0.0114 0.8381 12.000 1.0673 0.03402 0.02736 0.0041 0.0097 0.8398 12.250 1.0763 0.03537 0.02874 0.0049 0.0084 0.8416 12.500 1.0861 0.03669 0.03011 0.0055 0.0078 0.8434 12.750 1.0964 0.03802 0.03148 0.0061 0.0075 0.8451 13.000 1.1069 0.03933 0.03283 0.0066 0.0071 0.8468 13.250 1.1163 0.04079 0.03433 0.0071 0.0068 0.8484 13.500 1.1255 0.04226 0.03584 0.0076 0.0066 0.8498 14.000 1.1438 0.04531 0.03900 0.0084 0.0063 0.8530 14.250 1.1509 0.04705 0.04079 0.0088 0.0060 0.8547 14.500 1.1599 0.04865 0.04245 0.0091 0.0059 0.8566 14.750 1.1686 0.05031 0.04418 0.0093 0.0057 0.8585 15.000 1.1777 0.05193 0.04585 0.0095 0.0057 0.8604 15.250 1.1848 0.05379 0.04777 0.0097 0.0054 0.8623 15.500 1.1931 0.05557 0.04961 0.0098 0.0054 0.8643 16.000 1.2060 0.05957 0.05375 0.0100 0.0052 0.8688 16.250 1.2114 0.06169 0.05594 0.0100 0.0051 0.8713 16.500 1.2184 0.06370 0.05801 0.0099 0.0049 0.8739 16.750 1.2223 0.06608 0.06047 0.0098 0.0048 0.8764 17.000 1.2272 0.06838 0.06284 0.0096 0.0048 0.8791 17.500 1.2330 0.07354 0.06817 0.0091 0.0047 0.8849 17.750 1.2331 0.07651 0.07122 0.0088 0.0045 0.8884 18.000 1.2356 0.07925 0.07405 0.0083 0.0046 0.8923 18.250 1.2267 0.08351 0.07841 0.0077 0.0043 0.8958 18.500 1.2275 0.08658 0.08159 0.0070 0.0042 0.9003