XFOIL Version 6.96 Calculated polar for: WORTMANN FX 05-188 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.500 -0.4661 0.09146 0.08616 -0.0857 0.9839 0.0344 -13.250 -0.5002 0.08056 0.07501 -0.0944 0.9715 0.0340 -13.000 -0.5246 0.07260 0.06677 -0.1010 0.9602 0.0338 -12.750 -0.5403 0.06628 0.06014 -0.1063 0.9510 0.0337 -12.500 -0.5495 0.06091 0.05443 -0.1108 0.9431 0.0336 -12.250 -0.5535 0.05647 0.04965 -0.1143 0.9346 0.0337 -12.000 -0.5536 0.05255 0.04536 -0.1170 0.9265 0.0339 -11.750 -0.5495 0.04931 0.04178 -0.1187 0.9182 0.0340 -11.500 -0.5412 0.04642 0.03854 -0.1201 0.9111 0.0341 -11.250 -0.5322 0.04409 0.03591 -0.1203 0.9032 0.0343 -11.000 -0.5162 0.04180 0.03328 -0.1211 0.8975 0.0346 -10.750 -0.5008 0.03998 0.03120 -0.1209 0.8908 0.0349 -10.500 -0.4801 0.03831 0.02927 -0.1210 0.8851 0.0353 -10.250 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-0.250 0.2096 0.02755 0.01886 -0.0642 0.7171 0.7106 0.000 0.2445 0.02723 0.01844 -0.0664 0.7152 0.7174 0.250 0.2754 0.02715 0.01832 -0.0669 0.7136 0.7200 0.750 0.2908 0.02804 0.01926 -0.0610 0.7005 0.7281 1.000 0.3264 0.02779 0.01895 -0.0631 0.6985 0.7332 1.250 0.3605 0.02759 0.01871 -0.0643 0.6970 0.7364 1.750 0.3729 0.02857 0.01977 -0.0581 0.6829 0.7440 2.000 0.4098 0.02832 0.01949 -0.0600 0.6811 0.7480 2.250 0.4509 0.02797 0.01910 -0.0627 0.6796 0.7520 2.750 0.4587 0.02900 0.02023 -0.0557 0.6649 0.7588 3.000 0.4955 0.02873 0.01997 -0.0573 0.6634 0.7623 3.500 0.5150 0.02994 0.02125 -0.0537 0.6489 0.7702 3.750 0.5477 0.02963 0.02098 -0.0543 0.6473 0.7728 4.250 0.5702 0.03111 0.02256 -0.0514 0.6330 0.7808 4.500 0.6098 0.03069 0.02216 -0.0535 0.6316 0.7841 5.000 0.6293 0.03223 0.02387 -0.0498 0.6174 0.7900 5.250 0.6642 0.03176 0.02345 -0.0507 0.6160 0.7930 5.750 0.6967 0.03328 0.02511 -0.0499 0.6019 0.8002 6.000 0.7293 0.03272 0.02463 -0.0501 0.6004 0.8025 6.500 0.7564 0.03414 0.02622 -0.0478 0.5860 0.8087 6.750 0.7942 0.03348 0.02566 -0.0490 0.5845 0.8116 7.250 0.8278 0.03468 0.02705 -0.0478 0.5697 0.8175 7.750 0.8649 0.03522 0.02781 -0.0461 0.5545 0.8230 8.000 0.9110 0.03347 0.02615 -0.0474 0.5507 0.8257 8.250 0.9230 0.03412 0.02689 -0.0462 0.5376 0.8289 8.500 0.9372 0.03457 0.02743 -0.0452 0.5240 0.8317 8.750 0.9592 0.03435 0.02730 -0.0443 0.5129 0.8341 9.000 0.9901 0.03362 0.02665 -0.0442 0.5028 0.8366 9.250 0.9993 0.03455 0.02769 -0.0429 0.4879 0.8396 9.500 1.0154 0.03503 0.02824 -0.0421 0.4715 0.8426 9.750 1.0358 0.03525 0.02849 -0.0416 0.4532 0.8453 10.000 1.0424 0.03646 0.02975 -0.0403 0.4310 0.8476 10.250 1.0582 0.03668 0.02989 -0.0390 0.4014 0.8500 10.500 1.0676 0.03754 0.03059 -0.0374 0.3655 0.8529 10.750 1.0715 0.03900 0.03185 -0.0358 0.3237 0.8559 11.000 1.0702 0.04106 0.03363 -0.0342 0.2766 0.8587 11.250 1.0659 0.04362 0.03592 -0.0329 0.2343 0.8613 11.500 1.0609 0.04627 0.03837 -0.0315 0.1994 0.8635 11.750 1.0570 0.04895 0.04090 -0.0303 0.1698 0.8659 12.000 1.0558 0.05155 0.04340 -0.0295 0.1457 0.8684 12.250 1.0563 0.05413 0.04590 -0.0290 0.1249 0.8712 13.000 1.0617 0.06192 0.05359 -0.0280 0.0863 0.8804 13.250 1.0642 0.06446 0.05616 -0.0276 0.0782 0.8838 13.500 1.0659 0.06721 0.05892 -0.0275 0.0719 0.8871 13.750 1.0718 0.06962 0.06143 -0.0276 0.0662 0.8906 14.000 1.0755 0.07224 0.06410 -0.0276 0.0618 0.8940 14.250 1.0803 0.07456 0.06650 -0.0274 0.0583 0.8980 14.500 1.0869 0.07680 0.06884 -0.0273 0.0551 0.9026 14.750 1.0925 0.07926 0.07135 -0.0275 0.0525 0.9074 15.000 1.0984 0.08141 0.07359 -0.0274 0.0501 0.9132 15.250 1.1060 0.08342 0.07573 -0.0273 0.0480 0.9206 15.500 1.1116 0.08548 0.07787 -0.0270 0.0462 0.9311 15.750 1.1158 0.08735 0.07982 -0.0267 0.0450 0.9549 16.000 1.1250 0.08935 0.08183 -0.0273 0.0438 1.0000 16.250 1.1388 0.09130 0.08394 -0.0279 0.0425 1.0000 16.500 1.1511 0.09347 0.08624 -0.0287 0.0411 1.0000 16.750 1.1617 0.09587 0.08874 -0.0296 0.0399 1.0000 17.000 1.1710 0.09845 0.09139 -0.0307 0.0388 1.0000 17.250 1.1806 0.10091 0.09386 -0.0318 0.0378 1.0000 17.500 1.1911 0.10328 0.09631 -0.0327 0.0369 1.0000 17.750 1.1989 0.10614 0.09938 -0.0338 0.0362 1.0000 18.000 1.2052 0.10923 0.10269 -0.0350 0.0356 1.0000 18.250 1.2097 0.11259 0.10624 -0.0364 0.0350 1.0000 18.500 1.2118 0.11634 0.11017 -0.0381 0.0344 1.0000 18.750 1.2122 0.12036 0.11437 -0.0401 0.0339 1.0000 19.000 1.2113 0.12459 0.11876 -0.0424 0.0333 1.0000 19.250 1.2099 0.12892 0.12324 -0.0448 0.0329 1.0000