XFOIL Version 6.96 Calculated polar for: EPPLER 334 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.250 -0.3022 0.08612 0.08407 -0.0305 1.0000 0.0125 -8.000 -0.3075 0.08244 0.08044 -0.0327 1.0000 0.0126 -7.750 -0.3094 0.07846 0.07651 -0.0362 0.9942 0.0126 -7.500 -0.2880 0.07123 0.06919 -0.0483 0.9464 0.0127 -7.250 -0.2399 0.06255 0.06026 -0.0639 0.8996 0.0128 -7.000 -0.2272 0.05991 0.05735 -0.0651 0.8365 0.0131 -6.750 -0.2229 0.05731 0.05453 -0.0646 0.7982 0.0132 -6.500 -0.2171 0.05472 0.05175 -0.0640 0.7704 0.0134 -6.250 -0.2094 0.05203 0.04889 -0.0634 0.7472 0.0138 -6.000 -0.1998 0.04920 0.04588 -0.0629 0.7279 0.0140 -5.750 -0.1886 0.04634 0.04283 -0.0621 0.7108 0.0144 -5.500 -0.1749 0.04298 0.03922 -0.0611 0.6962 0.0154 -5.250 -0.1614 0.03807 0.03388 -0.0589 0.6843 0.0161 -5.000 -0.1472 0.03609 0.03178 -0.0580 0.6701 0.0164 -4.750 -0.1311 0.03441 0.02996 -0.0571 0.6565 0.0168 -4.500 -0.1130 0.03242 0.02777 -0.0559 0.6436 0.0179 -4.250 -0.0942 0.02869 0.02354 -0.0532 0.6333 0.0200 -4.000 -0.0750 0.02735 0.02211 -0.0525 0.6213 0.0207 -3.750 -0.0535 0.02586 0.02040 -0.0513 0.6102 0.0227 -3.500 -0.0325 0.02358 0.01777 -0.0497 0.6002 0.0250 -3.250 -0.0098 0.02250 0.01654 -0.0489 0.5898 0.0267 -3.000 0.0133 0.02089 0.01459 -0.0475 0.5795 0.0304 -2.750 0.0379 0.02015 0.01375 -0.0469 0.5695 0.0335 -2.500 0.0617 0.01892 0.01226 -0.0460 0.5604 0.0377 -2.250 0.0875 0.01863 0.01165 -0.0449 0.5512 0.0437 -2.000 0.1184 0.01397 0.00649 -0.0428 0.5443 0.0180 -1.750 0.1455 0.01303 0.00531 -0.0419 0.5356 0.0160 -1.500 0.1705 0.01245 0.00464 -0.0411 0.5275 0.0158 -1.250 0.1954 0.01188 0.00403 -0.0403 0.5192 0.0158 -0.750 0.2444 0.01103 0.00312 -0.0387 0.5046 0.0175 -0.500 0.2698 0.01084 0.00284 -0.0380 0.4973 0.0198 -0.250 0.2940 0.01034 0.00253 -0.0371 0.4905 0.0714 0.000 0.2883 0.00786 0.00265 -0.0307 0.4857 0.8464 0.250 0.3025 0.00826 0.00306 -0.0264 0.4801 0.9270 0.500 0.3491 0.00888 0.00361 -0.0286 0.4727 0.9628 0.750 0.4553 0.00942 0.00388 -0.0446 0.4625 0.9765 1.000 0.5235 0.00951 0.00385 -0.0531 0.4544 0.9863 1.250 0.5566 0.00954 0.00375 -0.0543 0.4484 0.9877 1.500 0.5889 0.00950 0.00368 -0.0554 0.4428 0.9892 1.750 0.6193 0.00952 0.00364 -0.0561 0.4375 0.9909 2.000 0.6486 0.00960 0.00362 -0.0566 0.4323 0.9925 2.250 0.6777 0.00961 0.00363 -0.0570 0.4272 0.9941 2.500 0.7079 0.00963 0.00361 -0.0577 0.4223 0.9954 2.750 0.7379 0.00972 0.00361 -0.0584 0.4173 0.9965 3.000 0.7684 0.00971 0.00362 -0.0591 0.4126 0.9978 3.250 0.7979 0.00975 0.00364 -0.0597 0.4079 0.9990 3.500 0.8271 0.00985 0.00369 -0.0602 0.4035 1.0000 3.750 0.8503 0.00994 0.00378 -0.0595 0.3991 1.0000 4.000 0.8737 0.01001 0.00386 -0.0587 0.3949 1.0000 4.250 0.8967 0.01011 0.00394 -0.0579 0.3903 1.0000 4.500 0.9192 0.01028 0.00408 -0.0570 0.3861 1.0000 4.750 0.9424 0.01033 0.00419 -0.0562 0.3820 1.0000 5.000 0.9652 0.01042 0.00428 -0.0554 0.3775 1.0000 5.250 0.9874 0.01056 0.00440 -0.0545 0.3731 1.0000 5.500 1.0097 0.01069 0.00456 -0.0535 0.3687 1.0000 5.750 1.0320 0.01077 0.00468 -0.0526 0.3642 1.0000 6.000 1.0538 0.01090 0.00481 -0.0516 0.3596 1.0000 6.250 1.0749 0.01109 0.00499 -0.0505 0.3551 1.0000 6.500 1.0966 0.01117 0.00515 -0.0495 0.3504 1.0000 6.750 1.1176 0.01130 0.00531 -0.0483 0.3457 1.0000 7.000 1.1372 0.01153 0.00550 -0.0469 0.3407 1.0000 7.250 1.1580 0.01161 0.00568 -0.0457 0.3360 1.0000 7.500 1.1777 0.01174 0.00585 -0.0443 0.3305 1.0000 7.750 1.1959 0.01195 0.00605 -0.0427 0.3248 1.0000 8.000 1.2151 0.01205 0.00624 -0.0412 0.3190 1.0000 8.250 1.2323 0.01224 0.00644 -0.0394 0.3133 1.0000 8.500 1.2494 0.01240 0.00666 -0.0375 0.3073 1.0000 8.750 1.2656 0.01256 0.00686 -0.0355 0.3005 1.0000 9.000 1.2804 0.01277 0.00710 -0.0332 0.2947 1.0000 9.250 1.2966 0.01293 0.00733 -0.0312 0.2877 1.0000 9.500 1.3119 0.01318 0.00758 -0.0291 0.2803 1.0000 9.750 1.3299 0.01340 0.00785 -0.0276 0.2718 1.0000 10.000 1.3483 0.01369 0.00817 -0.0262 0.2626 1.0000 10.250 1.3660 0.01405 0.00853 -0.0248 0.2525 1.0000 10.500 1.3839 0.01443 0.00892 -0.0234 0.2409 1.0000 10.750 1.4010 0.01486 0.00936 -0.0220 0.2281 1.0000 11.000 1.4165 0.01536 0.00986 -0.0204 0.2151 1.0000 11.250 1.4299 0.01591 0.01040 -0.0184 0.2022 1.0000 11.500 1.4399 0.01652 0.01100 -0.0159 0.1895 1.0000 11.750 1.4477 0.01725 0.01171 -0.0132 0.1760 1.0000 12.000 1.4543 0.01807 0.01252 -0.0105 0.1629 1.0000 12.250 1.4593 0.01902 0.01345 -0.0078 0.1505 1.0000 12.500 1.4628 0.02012 0.01454 -0.0052 0.1389 1.0000 12.750 1.4643 0.02142 0.01584 -0.0028 0.1279 1.0000 13.000 1.4641 0.02297 0.01740 -0.0007 0.1184 1.0000 13.250 1.4636 0.02474 0.01918 0.0010 0.1092 1.0000 13.500 1.4628 0.02672 0.02120 0.0023 0.1007 1.0000 13.750 1.4594 0.02911 0.02362 0.0032 0.0931 1.0000 14.000 1.4548 0.03181 0.02635 0.0038 0.0860 1.0000 14.250 1.4514 0.03455 0.02915 0.0042 0.0801 1.0000 14.500 1.4433 0.03789 0.03253 0.0043 0.0746 1.0000 14.750 1.4377 0.04109 0.03579 0.0042 0.0691 1.0000 15.000 1.4279 0.04482 0.03957 0.0039 0.0650 1.0000 15.250 1.4210 0.04832 0.04316 0.0035 0.0613 1.0000 15.500 1.4109 0.05226 0.04715 0.0030 0.0573 1.0000 15.750 1.3987 0.05658 0.05153 0.0022 0.0542 1.0000 16.000 1.3926 0.06030 0.05534 0.0014 0.0510 1.0000 16.250 1.3814 0.06478 0.05987 0.0003 0.0478 1.0000 16.500 1.3709 0.06927 0.06444 -0.0009 0.0452 1.0000 16.750 1.3640 0.07338 0.06863 -0.0021 0.0422 1.0000 17.000 1.3524 0.07825 0.07354 -0.0036 0.0397 1.0000 17.250 1.3430 0.08289 0.07826 -0.0051 0.0377 1.0000 17.500 1.3365 0.08721 0.08267 -0.0066 0.0354 1.0000