XFOIL Version 6.96 Calculated polar for: WORTMANN FX 082-512 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 ------ -------- --------- --------- -------- -------- -------- -14.000 -0.6885 0.09974 0.09570 -0.0504 1.0000 0.0153 -13.750 -0.7133 0.09121 0.08701 -0.0545 1.0000 0.0151 -13.500 -0.7306 0.08487 0.08058 -0.0573 1.0000 0.0153 -13.250 -0.7453 0.07937 0.07496 -0.0595 1.0000 0.0153 -13.000 -0.7576 0.07462 0.07012 -0.0613 1.0000 0.0155 -12.750 -0.7688 0.07038 0.06581 -0.0626 1.0000 0.0158 -12.500 -0.7793 0.06657 0.06190 -0.0634 1.0000 0.0159 -12.250 -0.7893 0.06317 0.05844 -0.0639 1.0000 0.0162 -12.000 -0.7999 0.06011 0.05532 -0.0639 1.0000 0.0165 -11.750 -0.8107 0.05732 0.05247 -0.0635 1.0000 0.0168 -11.500 -0.8223 0.05472 0.04983 -0.0627 1.0000 0.0171 -11.250 -0.8345 0.05238 0.04743 -0.0614 1.0000 0.0174 -11.000 -0.8495 0.05021 0.04522 -0.0594 1.0000 0.0176 -10.750 -0.8470 0.04747 0.04237 -0.0618 0.9968 0.0181 -10.500 -0.8376 0.04459 0.03937 -0.0653 0.9933 0.0190 -10.250 -0.8233 0.04171 0.03635 -0.0693 0.9893 0.0197 -10.000 -0.8026 0.03889 0.03336 -0.0742 0.9862 0.0208 -9.750 -0.7809 0.03636 0.03065 -0.0785 0.9832 0.0219 -9.500 -0.7557 0.03287 0.02711 -0.0854 0.9795 0.0248 -9.250 -0.7238 0.03029 0.02445 -0.0916 0.9774 0.0284 -9.000 -0.6881 0.02797 0.02205 -0.0979 0.9759 0.0332 -8.750 -0.6512 0.02640 0.02036 -0.1031 0.9748 0.0407 -8.500 -0.6185 0.02548 0.01927 -0.1063 0.9730 0.0479 -8.250 -0.5881 0.02467 0.01830 -0.1086 0.9705 0.0531 -8.000 -0.5559 0.02409 0.01747 -0.1110 0.9683 0.0583 -7.750 -0.5228 0.02321 0.01653 -0.1138 0.9665 0.0627 -7.500 -0.4889 0.02260 0.01576 -0.1162 0.9649 0.0673 -7.250 -0.4544 0.02201 0.01497 -0.1187 0.9635 0.0717 -7.000 -0.4197 0.02132 0.01425 -0.1213 0.9623 0.0760 -6.750 -0.3871 0.02079 0.01360 -0.1231 0.9607 0.0791 -6.500 -0.3591 0.02023 0.01299 -0.1240 0.9575 0.0813 -6.250 -0.3269 0.01962 0.01236 -0.1259 0.9553 0.0835 -6.000 -0.2929 0.01910 0.01179 -0.1279 0.9533 0.0854 -5.750 -0.2579 0.01864 0.01124 -0.1301 0.9516 0.0874 -5.500 -0.2218 0.01814 0.01065 -0.1326 0.9501 0.0897 -5.250 -0.1849 0.01762 0.01004 -0.1353 0.9489 0.0930 -5.000 -0.1481 0.01721 0.00952 -0.1377 0.9478 0.0964 -4.750 -0.1147 0.01675 0.00898 -0.1395 0.9457 0.1003 -4.500 -0.0855 0.01638 0.00854 -0.1403 0.9420 0.1063 -4.250 -0.0445 0.01512 0.00786 -0.1449 0.9410 0.2470 -4.000 -0.0132 0.01517 0.00789 -0.1456 0.9381 0.2792 -3.750 0.0199 0.01524 0.00791 -0.1466 0.9357 0.2938 -3.500 0.0541 0.01526 0.00785 -0.1479 0.9339 0.3028 -3.250 0.0889 0.01530 0.00786 -0.1492 0.9323 0.3095 -3.000 0.1171 0.01537 0.00788 -0.1493 0.9286 0.3153 -2.750 0.1443 0.01543 0.00789 -0.1492 0.9239 0.3206 -2.500 0.1759 0.01546 0.00794 -0.1499 0.9209 0.3246 -2.250 0.2097 0.01540 0.00785 -0.1511 0.9187 0.3286 -2.000 0.2450 0.01529 0.00766 -0.1526 0.9170 0.3328 -1.750 0.2803 0.01516 0.00756 -0.1540 0.9155 0.3354 -1.500 0.3031 0.01527 0.00773 -0.1530 0.9089 0.3386 -1.250 0.3361 0.01513 0.00760 -0.1538 0.9043 0.3428 -1.000 0.3773 0.01468 0.00712 -0.1561 0.9005 0.3466 -0.750 0.4088 0.01444 0.00690 -0.1566 0.8933 0.3497 -0.500 0.4397 0.01429 0.00683 -0.1570 0.8874 0.3526 -0.250 0.4777 0.01400 0.00660 -0.1588 0.8835 0.3557 0.000 0.5053 0.01386 0.00649 -0.1585 0.8744 0.3577 0.250 0.5426 0.01353 0.00618 -0.1601 0.8674 0.3597 0.500 0.5729 0.01331 0.00598 -0.1603 0.8549 0.3616 0.750 0.6088 0.01301 0.00568 -0.1616 0.8406 0.3634 1.000 0.6545 0.01255 0.00522 -0.1647 0.8147 0.3652 1.250 0.7106 0.01225 0.00479 -0.1700 0.7617 0.3673 1.500 0.7498 0.01246 0.00463 -0.1718 0.6786 0.3693 1.750 0.7689 0.01304 0.00476 -0.1697 0.5890 0.3711 2.000 0.7756 0.01407 0.00512 -0.1652 0.4587 0.3728 2.250 0.7842 0.01524 0.00564 -0.1616 0.3316 0.3747 2.500 0.7919 0.01687 0.00634 -0.1582 0.1402 0.3766 2.750 0.8122 0.01754 0.00681 -0.1568 0.1081 0.3787 3.000 0.8358 0.01790 0.00716 -0.1560 0.1014 0.3806 3.250 0.8594 0.01822 0.00755 -0.1551 0.0977 0.3823 3.500 0.8831 0.01853 0.00796 -0.1543 0.0947 0.3842 3.750 0.9057 0.01893 0.00842 -0.1533 0.0920 0.3863 4.000 0.9280 0.01932 0.00888 -0.1522 0.0894 0.3885 4.250 0.9498 0.01973 0.00938 -0.1510 0.0869 0.3909 4.500 0.9703 0.02022 0.00992 -0.1496 0.0849 0.3934 4.750 0.9897 0.02083 0.01054 -0.1480 0.0830 0.3959 5.000 1.0117 0.02121 0.01104 -0.1469 0.0790 0.3986 5.250 1.0313 0.02183 0.01168 -0.1455 0.0744 0.4013 5.500 1.0545 0.02209 0.01212 -0.1446 0.0701 0.4044 5.750 1.0762 0.02251 0.01263 -0.1435 0.0658 0.4077 6.000 1.0967 0.02307 0.01324 -0.1422 0.0617 0.4109 6.250 1.1201 0.02329 0.01361 -0.1413 0.0566 0.4141 6.500 1.1432 0.02352 0.01400 -0.1405 0.0512 0.4174 6.750 1.1668 0.02371 0.01431 -0.1397 0.0444 0.4213 7.000 1.1890 0.02407 0.01472 -0.1387 0.0376 0.4256 7.500 1.2280 0.02537 0.01603 -0.1359 0.0280 0.4348 7.750 1.2457 0.02628 0.01709 -0.1342 0.0256 0.4404 8.250 1.2807 0.02826 0.01932 -0.1308 0.0216 0.4530 8.500 1.2966 0.02952 0.02069 -0.1290 0.0196 0.4606 8.750 1.3117 0.03114 0.02253 -0.1271 0.0182 0.4689 9.250 1.3477 0.03382 0.02568 -0.1242 0.0168 0.4954 9.500 1.3653 0.03533 0.02746 -0.1228 0.0161 0.5179 9.750 1.3817 0.03680 0.02922 -0.1213 0.0153 0.5563 10.000 1.3965 0.03814 0.03088 -0.1196 0.0146 0.6307 10.250 1.4030 0.03902 0.03227 -0.1163 0.0140 0.8283 10.750 1.4140 0.04229 0.03586 -0.1104 0.0131 1.0000 11.000 1.4180 0.04534 0.03916 -0.1079 0.0127 1.0000 11.250 1.4236 0.04780 0.04187 -0.1056 0.0124 1.0000 11.500 1.4260 0.05056 0.04491 -0.1032 0.0122 1.0000 11.750 1.4248 0.05367 0.04836 -0.1006 0.0121 1.0000 12.000 1.4200 0.05712 0.05211 -0.0982 0.0119 1.0000 12.250 1.4111 0.06106 0.05635 -0.0959 0.0117 1.0000 12.500 1.3986 0.06547 0.06108 -0.0940 0.0116 1.0000 12.750 1.3829 0.07041 0.06632 -0.0927 0.0116 1.0000 13.000 1.3633 0.07613 0.07234 -0.0922 0.0115 1.0000 13.250 1.3412 0.08257 0.07906 -0.0929 0.0115 1.0000 13.500 1.3165 0.08994 0.08671 -0.0949 0.0115 1.0000 13.750 1.2893 0.09861 0.09564 -0.0988 0.0116 1.0000 14.000 1.2588 0.10922 0.10651 -0.1050 0.0117 1.0000 14.250 1.2228 0.12335 0.12086 -0.1148 0.0119 1.0000