XFOIL Version 6.96 Calculated polar for: EPPLER 559 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.250 -0.8039 0.08675 0.08362 -0.0594 1.0000 0.0125 -16.000 -0.8092 0.08276 0.07958 -0.0611 1.0000 0.0126 -15.750 -0.8155 0.07862 0.07539 -0.0629 1.0000 0.0128 -15.500 -0.8209 0.07481 0.07153 -0.0644 1.0000 0.0128 -15.250 -0.8285 0.07073 0.06740 -0.0661 1.0000 0.0130 -15.000 -0.8368 0.06675 0.06336 -0.0677 1.0000 0.0131 -14.750 -0.8440 0.06295 0.05951 -0.0691 1.0000 0.0133 -14.500 -0.8534 0.05917 0.05566 -0.0704 1.0000 0.0134 -14.250 -0.8675 0.05519 0.05163 -0.0716 1.0000 0.0134 -14.000 -0.8810 0.05137 0.04775 -0.0725 1.0000 0.0135 -13.750 -0.8982 0.04743 0.04374 -0.0733 1.0000 0.0136 -13.500 -0.9167 0.04365 0.03990 -0.0735 1.0000 0.0136 -13.250 -0.9405 0.03991 0.03610 -0.0730 1.0000 0.0136 -13.000 -0.9528 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0.0288 -8.250 -0.3618 0.01031 0.00521 -0.1313 0.9186 0.0377 -8.000 -0.3137 0.00953 0.00454 -0.1362 0.9068 0.0632 -7.750 -0.2726 0.00904 0.00408 -0.1393 0.8884 0.0844 -7.500 -0.2401 0.00878 0.00377 -0.1404 0.8661 0.0999 -7.250 -0.2124 0.00858 0.00353 -0.1404 0.8438 0.1133 -7.000 -0.1859 0.00842 0.00332 -0.1401 0.8233 0.1264 -6.750 -0.1598 0.00828 0.00314 -0.1398 0.8046 0.1393 -6.500 -0.1336 0.00815 0.00297 -0.1394 0.7868 0.1523 -6.250 -0.1074 0.00805 0.00283 -0.1390 0.7698 0.1643 -6.000 -0.0807 0.00797 0.00270 -0.1387 0.7541 0.1759 -5.750 -0.0539 0.00791 0.00259 -0.1384 0.7391 0.1861 -5.500 -0.0270 0.00783 0.00249 -0.1381 0.7242 0.1962 -5.250 0.0001 0.00780 0.00240 -0.1378 0.7102 0.2055 -5.000 0.0272 0.00776 0.00232 -0.1376 0.6970 0.2153 -4.500 0.0820 0.00771 0.00218 -0.1371 0.6706 0.2323 -4.250 0.1096 0.00768 0.00212 -0.1370 0.6586 0.2415 -4.000 0.1371 0.00770 0.00208 -0.1368 0.6470 0.2497 -3.750 0.1648 0.00767 0.00202 -0.1366 0.6351 0.2575 -3.500 0.1927 0.00768 0.00198 -0.1365 0.6238 0.2645 -3.250 0.2203 0.00768 0.00194 -0.1363 0.6129 0.2710 -3.000 0.2482 0.00769 0.00191 -0.1362 0.6023 0.2784 -2.750 0.2762 0.00771 0.00189 -0.1361 0.5923 0.2843 -2.500 0.3037 0.00772 0.00187 -0.1359 0.5817 0.2917 -2.250 0.3319 0.00774 0.00186 -0.1358 0.5717 0.2982 -2.000 0.3597 0.00776 0.00185 -0.1357 0.5625 0.3055 -1.750 0.3877 0.00779 0.00185 -0.1356 0.5530 0.3125 -1.500 0.4156 0.00782 0.00184 -0.1355 0.5440 0.3187 -1.250 0.4433 0.00785 0.00186 -0.1353 0.5343 0.3264 -1.000 0.4713 0.00790 0.00187 -0.1352 0.5261 0.3323 -0.750 0.4990 0.00793 0.00189 -0.1351 0.5175 0.3396 -0.500 0.5270 0.00798 0.00191 -0.1350 0.5094 0.3469 -0.250 0.5546 0.00803 0.00194 -0.1348 0.5007 0.3536 0.000 0.5825 0.00807 0.00198 -0.1347 0.4931 0.3607 0.250 0.6102 0.00814 0.00201 -0.1346 0.4854 0.3673 0.500 0.6379 0.00818 0.00206 -0.1345 0.4783 0.3753 0.750 0.6656 0.00825 0.00211 -0.1343 0.4707 0.3823 1.000 0.6929 0.00832 0.00216 -0.1341 0.4634 0.3898 1.250 0.7208 0.00837 0.00222 -0.1340 0.4569 0.3978 1.500 0.7479 0.00846 0.00229 -0.1338 0.4500 0.4054 1.750 0.7757 0.00851 0.00235 -0.1337 0.4441 0.4137 2.000 0.8031 0.00858 0.00243 -0.1335 0.4373 0.4220 2.250 0.8300 0.00868 0.00251 -0.1333 0.4309 0.4313 2.500 0.8577 0.00873 0.00259 -0.1332 0.4255 0.4401 2.750 0.8847 0.00882 0.00268 -0.1329 0.4195 0.4503 3.000 0.9116 0.00890 0.00278 -0.1327 0.4139 0.4612 3.250 0.9390 0.00897 0.00287 -0.1325 0.4083 0.4726 3.500 0.9656 0.00907 0.00299 -0.1322 0.4026 0.4853 3.750 0.9924 0.00916 0.00311 -0.1320 0.3975 0.5001 4.000 1.0196 0.00921 0.00322 -0.1318 0.3924 0.5165 4.250 1.0459 0.00932 0.00335 -0.1315 0.3867 0.5343 4.500 1.0722 0.00942 0.00349 -0.1311 0.3817 0.5554 4.750 1.0992 0.00947 0.00362 -0.1310 0.3768 0.5805 5.000 1.1252 0.00956 0.00378 -0.1306 0.3714 0.6093 5.500 1.1775 0.00970 0.00411 -0.1299 0.3617 0.6844 5.750 1.2030 0.00976 0.00429 -0.1295 0.3565 0.7353 6.000 1.2264 0.00985 0.00451 -0.1286 0.3508 0.7979 6.250 1.2455 0.00971 0.00466 -0.1266 0.3470 0.9063 6.500 1.2699 0.00976 0.00478 -0.1258 0.3419 1.0000 6.750 1.2941 0.00998 0.00496 -0.1251 0.3361 1.0000 7.000 1.3198 0.01013 0.00512 -0.1247 0.3316 1.0000 7.250 1.3448 0.01030 0.00529 -0.1242 0.3260 1.0000 7.500 1.3679 0.01055 0.00551 -0.1233 0.3197 1.0000 7.750 1.3927 0.01070 0.00568 -0.1228 0.3149 1.0000 8.000 1.4158 0.01090 0.00587 -0.1219 0.3090 1.0000 8.250 1.4370 0.01116 0.00610 -0.1207 0.3025 1.0000 8.500 1.4602 0.01133 0.00630 -0.1198 0.2971 1.0000 8.750 1.4809 0.01160 0.00654 -0.1185 0.2901 1.0000 9.000 1.5025 0.01183 0.00679 -0.1174 0.2840 1.0000 9.250 1.5231 0.01210 0.00705 -0.1161 0.2770 1.0000 9.500 1.5431 0.01240 0.00733 -0.1148 0.2700 1.0000 9.750 1.5630 0.01270 0.00763 -0.1135 0.2615 1.0000 10.000 1.5818 0.01305 0.00796 -0.1119 0.2533 1.0000 10.250 1.5991 0.01345 0.00833 -0.1102 0.2438 1.0000 10.500 1.6172 0.01382 0.00870 -0.1086 0.2343 1.0000 10.750 1.6321 0.01434 0.00916 -0.1066 0.2216 1.0000 11.000 1.6454 0.01493 0.00969 -0.1044 0.2085 1.0000 11.250 1.6571 0.01559 0.01030 -0.1019 0.1943 1.0000 11.500 1.6670 0.01635 0.01098 -0.0993 0.1802 1.0000 11.750 1.6749 0.01721 0.01178 -0.0965 0.1657 1.0000 12.000 1.6818 0.01814 0.01265 -0.0937 0.1527 1.0000 12.250 1.6872 0.01918 0.01364 -0.0908 0.1400 1.0000 12.500 1.6918 0.02031 0.01473 -0.0880 0.1286 1.0000 12.750 1.6959 0.02153 0.01592 -0.0853 0.1176 1.0000 13.000 1.6990 0.02288 0.01723 -0.0828 0.1076 1.0000 13.250 1.7015 0.02435 0.01869 -0.0803 0.0993 1.0000 13.500 1.7026 0.02601 0.02034 -0.0780 0.0914 1.0000 13.750 1.7056 0.02763 0.02198 -0.0761 0.0848 1.0000 14.000 1.7045 0.02967 0.02401 -0.0741 0.0780 1.0000 14.250 1.7045 0.03175 0.02611 -0.0725 0.0719 1.0000 14.500 1.7036 0.03402 0.02840 -0.0710 0.0667 1.0000 14.750 1.7036 0.03635 0.03077 -0.0699 0.0625 1.0000 15.000 1.6999 0.03913 0.03357 -0.0688 0.0577 1.0000 15.250 1.6986 0.04180 0.03629 -0.0681 0.0541 1.0000 15.500 1.6933 0.04502 0.03954 -0.0675 0.0505 1.0000 15.750 1.6912 0.04803 0.04261 -0.0671 0.0475 1.0000 16.000 1.6863 0.05144 0.04608 -0.0669 0.0447 1.0000 16.250 1.6792 0.05526 0.04995 -0.0669 0.0418 1.0000 16.500 1.6755 0.05880 0.05356 -0.0671 0.0395 1.0000 16.750 1.6682 0.06287 0.05770 -0.0675 0.0372 1.0000 17.000 1.6604 0.06714 0.06203 -0.0681 0.0351 1.0000 17.250 1.6553 0.07117 0.06613 -0.0688 0.0333 1.0000 17.500 1.6470 0.07573 0.07076 -0.0698 0.0314 1.0000 17.750 1.6373 0.08059 0.07569 -0.0710 0.0296 1.0000 18.000 1.6318 0.08493 0.08011 -0.0721 0.0281 1.0000 18.250 1.6237 0.08976 0.08500 -0.0735 0.0265 1.0000 18.500 1.6137 0.09494 0.09025 -0.0751 0.0249 1.0000