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 = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.750 -0.2029 0.09890 0.09488 -0.0951 0.8256 0.0585 -11.500 -0.2014 0.09515 0.09103 -0.0971 0.8153 0.0609 -11.250 -0.2063 0.09060 0.08644 -0.1000 0.8068 0.0626 -11.000 -0.1655 0.07925 0.07521 -0.0953 0.7785 0.0677 -10.750 -0.1601 0.07623 0.07217 -0.0956 0.7745 0.0689 -10.500 -0.1602 0.07249 0.06838 -0.0966 0.7712 0.0710 -10.250 -0.1737 0.06650 0.06240 -0.0999 0.7686 0.0727 -10.000 -0.2055 0.05861 0.05450 -0.1051 0.7664 0.0732 -9.750 -0.2364 0.05313 0.04895 -0.1068 0.7634 0.0732 -9.500 -0.2652 0.04904 0.04477 -0.1063 0.7603 0.0737 -9.250 -0.2916 0.04601 0.04160 -0.1043 0.7572 0.0746 -9.000 -0.3239 0.04409 0.03948 -0.0996 0.7543 0.0761 -7.750 -0.3818 0.03516 0.02819 -0.0850 0.7448 0.0419 -7.500 -0.3673 0.03232 0.02500 -0.0832 0.7421 0.0401 -7.250 -0.3516 0.02973 0.02161 -0.0803 0.7398 0.0365 -7.000 -0.3266 0.02833 0.01997 -0.0798 0.7374 0.0358 -6.750 -0.2995 0.02629 0.01778 -0.0798 0.7346 0.0354 -6.500 -0.2713 0.02480 0.01614 -0.0799 0.7317 0.0354 -6.250 -0.2422 0.02361 0.01482 -0.0801 0.7292 0.0357 -6.000 -0.2120 0.02246 0.01360 -0.0805 0.7269 0.0362 -5.750 -0.1833 0.02118 0.01236 -0.0809 0.7249 0.0375 -5.500 -0.1605 0.02056 0.01175 -0.0803 0.7230 0.0399 -5.250 -0.1387 0.02016 0.01129 -0.0795 0.7212 0.0430 -5.000 -0.1218 0.01952 0.01069 -0.0778 0.7189 0.0455 -4.750 -0.1058 0.01902 0.01022 -0.0761 0.7163 0.0492 -4.500 -0.0894 0.01855 0.00974 -0.0743 0.7138 0.0562 -4.250 -0.0796 0.01762 0.00916 -0.0714 0.7116 0.1071 -4.000 -0.0884 0.01587 0.00868 -0.0662 0.7097 0.3566 -3.750 -0.0891 0.01506 0.00938 -0.0600 0.7080 0.6498 -3.500 -0.0632 0.01605 0.01039 -0.0582 0.7065 0.7309 -3.250 -0.0393 0.01729 0.01155 -0.0560 0.7047 0.7661 -3.000 -0.0092 0.01897 0.01320 -0.0540 0.7024 0.7886 -2.750 0.0251 0.02026 0.01444 -0.0532 0.7001 0.8041 -2.500 0.0541 0.02108 0.01517 -0.0524 0.6982 0.8179 -2.250 0.1159 0.02213 0.01609 -0.0568 0.6966 0.8268 -2.000 0.1576 0.02255 0.01639 -0.0587 0.6948 0.8369 -1.750 0.1765 0.02278 0.01655 -0.0570 0.6928 0.8489 -1.500 0.2354 0.02284 0.01646 -0.0628 0.6912 0.8517 -1.250 0.2779 0.02292 0.01643 -0.0658 0.6898 0.8563 -1.000 0.2886 0.02310 0.01661 -0.0630 0.6880 0.8654 -0.750 0.3279 0.02320 0.01669 -0.0657 0.6857 0.8690 -0.500 0.3232 0.02344 0.01697 -0.0601 0.6829 0.8791 -0.250 0.3679 0.02340 0.01688 -0.0638 0.6808 0.8814 0.000 0.4033 0.02342 0.01686 -0.0658 0.6789 0.8849 0.250 0.4170 0.02352 0.01693 -0.0636 0.6771 0.8911 0.500 0.4387 0.02350 0.01687 -0.0629 0.6753 0.8955 0.750 0.4770 0.02346 0.01678 -0.0654 0.6737 0.8979 1.000 0.4947 0.02378 0.01714 -0.0643 0.6712 0.9021 1.250 0.4764 0.02429 0.01775 -0.0565 0.6675 0.9091 1.500 0.5085 0.02440 0.01787 -0.0581 0.6646 0.9113 1.750 0.5352 0.02447 0.01795 -0.0586 0.6624 0.9139 2.000 0.5549 0.02449 0.01796 -0.0575 0.6604 0.9171 2.250 0.5458 0.02452 0.01796 -0.0507 0.6585 0.9222 2.500 0.5859 0.02454 0.01794 -0.0536 0.6570 0.9233 2.750 0.5615 0.02574 0.01935 -0.0458 0.6499 0.9282 3.000 0.5209 0.02589 0.01952 -0.0335 0.6458 0.9350 3.250 0.5589 0.02578 0.01940 -0.0357 0.6441 0.9360 3.500 0.5997 0.02557 0.01917 -0.0384 0.6427 0.9368 3.750 0.6372 0.02543 0.01900 -0.0404 0.6412 0.9376 4.000 0.5342 0.02720 0.02095 -0.0192 0.6292 0.9482 4.250 0.5738 0.02690 0.02065 -0.0214 0.6279 0.9487 4.500 0.6178 0.02650 0.02025 -0.0243 0.6268 0.9490 4.750 0.6633 0.02615 0.01989 -0.0274 0.6257 0.9494 5.000 0.5904 0.02827 0.02214 -0.0128 0.6125 0.9586 5.250 0.6359 0.02769 0.02158 -0.0156 0.6116 0.9588 5.500 0.6838 0.02709 0.02100 -0.0188 0.6108 0.9588 5.750 0.7338 0.02647 0.02038 -0.0224 0.6098 0.9588 6.000 0.6314 0.03161 0.02572 -0.0076 0.5868 0.9710 6.250 0.6935 0.02991 0.02405 -0.0115 0.5886 0.9699 6.500 0.7624 0.02835 0.02253 -0.0170 0.5900 0.9681 6.750 0.8408 0.02655 0.02074 -0.0241 0.5921 0.9658 7.000 0.8226 0.02780 0.02211 -0.0183 0.5819 0.9716 7.250 0.8846 0.02640 0.02077 -0.0231 0.5810 0.9706 7.500 0.9468 0.02493 0.01933 -0.0281 0.5795 0.9696 7.750 0.9428 0.02598 0.02054 -0.0245 0.5698 0.9744 8.000 0.9960 0.02471 0.01932 -0.0281 0.5670 0.9743 8.250 1.0555 0.02313 0.01778 -0.0326 0.5643 0.9738 8.500 1.0739 0.02324 0.01805 -0.0319 0.5555 0.9768 8.750 1.1243 0.02188 0.01675 -0.0352 0.5502 0.9771 9.000 1.1465 0.02165 0.01667 -0.0347 0.5418 0.9801 9.250 1.1904 0.02034 0.01539 -0.0369 0.5336 0.9811 9.500 1.2024 0.02014 0.01534 -0.0348 0.5208 0.9860 9.750 1.2182 0.01973 0.01503 -0.0333 0.5051 0.9918 10.000 1.2192 0.01969 0.01504 -0.0294 0.4882 1.0000 10.250 1.1974 0.02008 0.01544 -0.0219 0.4761 1.0000 10.500 1.1928 0.02064 0.01598 -0.0179 0.4547 1.0000 10.750 1.1970 0.02124 0.01647 -0.0153 0.4286 1.0000 11.000 1.1940 0.02250 0.01755 -0.0124 0.3959 1.0000 11.250 1.1876 0.02427 0.01913 -0.0097 0.3636 1.0000 11.500 1.1785 0.02647 0.02114 -0.0072 0.3327 1.0000 11.750 1.1700 0.02882 0.02335 -0.0051 0.3050 1.0000 12.000 1.1611 0.03134 0.02571 -0.0032 0.2783 1.0000 12.250 1.1518 0.03403 0.02825 -0.0016 0.2511 1.0000 12.500 1.1457 0.03660 0.03070 -0.0003 0.2262 1.0000 12.750 1.1401 0.03925 0.03324 0.0008 0.2033 1.0000 13.000 1.1367 0.04183 0.03572 0.0017 0.1812 1.0000 13.250 1.1329 0.04454 0.03832 0.0024 0.1603 1.0000 13.500 1.1307 0.04718 0.04088 0.0030 0.1396 1.0000 13.750 1.1275 0.05001 0.04360 0.0035 0.1204 1.0000 14.000 1.1219 0.05315 0.04660 0.0040 0.0963 1.0000 14.250 1.1145 0.05656 0.04984 0.0044 0.0728 1.0000 14.500 1.1029 0.06050 0.05361 0.0049 0.0525 1.0000 14.750 1.0948 0.06425 0.05728 0.0052 0.0427 1.0000 15.000 1.0914 0.06759 0.06065 0.0053 0.0369 1.0000 15.250 1.0868 0.07109 0.06415 0.0052 0.0343 1.0000 15.500 1.0879 0.07403 0.06717 0.0051 0.0320 1.0000 15.750 1.0900 0.07686 0.07007 0.0048 0.0304 1.0000 16.000 1.0903 0.07994 0.07319 0.0045 0.0285 1.0000 16.250 1.0927 0.08265 0.07592 0.0043 0.0279 1.0000 16.500 1.0973 0.08497 0.07825 0.0045 0.0269 1.0000 16.750 1.1042 0.08723 0.08062 0.0044 0.0259 1.0000 17.000 1.1122 0.08927 0.08276 0.0044 0.0252 1.0000 17.250 1.1206 0.09128 0.08485 0.0044 0.0244 1.0000 17.500 1.1299 0.09313 0.08676 0.0044 0.0238 1.0000 17.750 1.1392 0.09498 0.08865 0.0043 0.0232 1.0000 18.000 1.1526 0.09606 0.08967 0.0048 0.0221 1.0000 18.250 1.1654 0.09751 0.09122 0.0053 0.0218 1.0000 18.500 1.1666 0.10079 0.09471 0.0044 0.0215 1.0000 18.750 1.1660 0.10437 0.09849 0.0034 0.0211 1.0000 19.000 1.1668 0.10775 0.10208 0.0026 0.0210 1.0000 19.250 1.1652 0.11156 0.10608 0.0014 0.0209 1.0000