XFOIL Version 6.96 Calculated polar for: EPPLER 555 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 ------ -------- --------- --------- -------- -------- -------- -15.250 -0.5993 0.11346 0.10930 -0.0439 1.0000 0.0093 -15.000 -0.6457 0.09864 0.09419 -0.0520 1.0000 0.0091 -14.750 -0.6711 0.08974 0.08509 -0.0568 1.0000 0.0090 -14.500 -0.6897 0.08280 0.07794 -0.0603 1.0000 0.0089 -14.250 -0.7048 0.07691 0.07188 -0.0630 1.0000 0.0089 -14.000 -0.7162 0.07194 0.06675 -0.0652 1.0000 0.0089 -13.750 -0.7257 0.06753 0.06218 -0.0668 1.0000 0.0090 -13.500 -0.7332 0.06359 0.05808 -0.0680 1.0000 0.0089 -13.250 -0.7392 0.06014 0.05449 -0.0688 1.0000 0.0090 -13.000 -0.7429 0.05709 0.05132 -0.0692 1.0000 0.0091 -12.750 -0.7457 0.05424 0.04834 -0.0694 1.0000 0.0092 -12.500 -0.7473 0.05163 0.04561 -0.0693 1.0000 0.0093 -12.250 -0.7472 0.04931 0.04318 -0.0689 1.0000 0.0093 -12.000 -0.7469 0.04710 0.04086 -0.0684 1.0000 0.0095 -11.750 -0.7459 0.04506 0.03872 -0.0675 1.0000 0.0097 -11.500 -0.7443 0.04320 0.03678 -0.0665 1.0000 0.0098 -11.250 -0.7426 0.04147 0.03496 -0.0653 1.0000 0.0099 -11.000 -0.7419 0.03979 0.03320 -0.0638 1.0000 0.0102 -10.750 -0.7421 0.03820 0.03154 -0.0621 1.0000 0.0104 -10.500 -0.7437 0.03670 0.02997 -0.0600 1.0000 0.0106 -10.250 -0.7481 0.03528 0.02852 -0.0575 1.0000 0.0107 -10.000 -0.7581 0.03388 0.02712 -0.0544 1.0000 0.0108 -9.750 -0.7562 0.03230 0.02551 -0.0537 0.9977 0.0111 -9.500 -0.7344 0.03049 0.02364 -0.0568 0.9915 0.0116 -9.250 -0.7095 0.02867 0.02171 -0.0602 0.9849 0.0123 -9.000 -0.6852 0.02698 0.01988 -0.0630 0.9772 0.0134 -8.750 -0.6581 0.02540 0.01827 -0.0660 0.9707 0.0147 -8.500 -0.6333 0.02402 0.01679 -0.0679 0.9628 0.0162 -8.250 -0.6068 0.02271 0.01542 -0.0699 0.9561 0.0180 -7.750 -0.5481 0.02033 0.01289 -0.0741 0.9445 0.0252 -7.500 -0.5220 0.01927 0.01182 -0.0753 0.9365 0.0316 -7.250 -0.4887 0.01821 0.01076 -0.0777 0.9322 0.0438 -7.000 -0.4607 0.01723 0.00985 -0.0791 0.9245 0.0623 -6.750 -0.4278 0.01611 0.00889 -0.0816 0.9190 0.0970 -6.500 -0.3937 0.01462 0.00775 -0.0849 0.9138 0.1704 -6.250 -0.3636 0.01300 0.00683 -0.0876 0.9059 0.3118 -6.000 -0.3242 0.01274 0.00667 -0.0902 0.9012 0.3716 -5.750 -0.2904 0.01269 0.00655 -0.0914 0.8933 0.3966 -5.500 -0.2520 0.01266 0.00638 -0.0935 0.8870 0.4161 -5.250 -0.2167 0.01269 0.00630 -0.0949 0.8792 0.4301 -5.000 -0.1803 0.01275 0.00629 -0.0965 0.8714 0.4416 -4.750 -0.1469 0.01291 0.00638 -0.0974 0.8623 0.4549 -4.500 -0.1116 0.01293 0.00623 -0.0989 0.8536 0.4644 -4.250 -0.0814 0.01285 0.00609 -0.0993 0.8430 0.4673 -4.000 -0.0492 0.01276 0.00590 -0.1001 0.8332 0.4703 -3.750 -0.0182 0.01267 0.00569 -0.1007 0.8227 0.4737 -3.500 0.0117 0.01258 0.00546 -0.1012 0.8120 0.4771 -3.250 0.0425 0.01249 0.00523 -0.1018 0.8020 0.4800 -3.000 0.0716 0.01243 0.00511 -0.1020 0.7912 0.4823 -2.750 0.1003 0.01240 0.00501 -0.1021 0.7806 0.4851 -2.500 0.1297 0.01237 0.00488 -0.1024 0.7705 0.4880 -2.250 0.1579 0.01233 0.00475 -0.1025 0.7596 0.4910 -2.000 0.1864 0.01230 0.00462 -0.1026 0.7489 0.4940 -1.750 0.2152 0.01228 0.00451 -0.1027 0.7388 0.4969 -1.500 0.2425 0.01227 0.00447 -0.1026 0.7278 0.4994 -1.250 0.2703 0.01227 0.00443 -0.1025 0.7174 0.5022 -0.750 0.3259 0.01228 0.00431 -0.1025 0.6964 0.5082 -0.500 0.3539 0.01230 0.00425 -0.1025 0.6862 0.5114 -0.250 0.3814 0.01232 0.00423 -0.1024 0.6761 0.5141 0.000 0.4084 0.01235 0.00426 -0.1022 0.6656 0.5170 0.250 0.4358 0.01239 0.00427 -0.1021 0.6558 0.5201 0.500 0.4631 0.01243 0.00428 -0.1020 0.6455 0.5234 0.750 0.4905 0.01248 0.00429 -0.1019 0.6353 0.5267 1.000 0.5177 0.01254 0.00430 -0.1018 0.6257 0.5298 1.250 0.5444 0.01259 0.00438 -0.1015 0.6151 0.5328 1.500 0.5712 0.01266 0.00445 -0.1013 0.6051 0.5363 1.750 0.5981 0.01275 0.00451 -0.1011 0.5953 0.5401 2.000 0.6249 0.01283 0.00458 -0.1009 0.5847 0.5439 2.250 0.6515 0.01292 0.00468 -0.1007 0.5748 0.5470 2.500 0.6777 0.01301 0.00478 -0.1004 0.5643 0.5503 2.750 0.7040 0.01311 0.00491 -0.1001 0.5537 0.5543 3.000 0.7302 0.01324 0.00502 -0.0998 0.5432 0.5588 3.250 0.7560 0.01336 0.00515 -0.0994 0.5321 0.5629 3.500 0.7816 0.01347 0.00531 -0.0990 0.5206 0.5667 3.750 0.8070 0.01361 0.00548 -0.0985 0.5092 0.5709 4.000 0.8323 0.01378 0.00562 -0.0980 0.4979 0.5756 4.250 0.8575 0.01392 0.00581 -0.0976 0.4858 0.5801 4.500 0.8822 0.01408 0.00603 -0.0970 0.4739 0.5849 4.750 0.9067 0.01427 0.00623 -0.0964 0.4617 0.5904 5.000 0.9309 0.01448 0.00644 -0.0958 0.4495 0.5957 5.250 0.9547 0.01467 0.00670 -0.0950 0.4365 0.6006 5.500 0.9785 0.01488 0.00695 -0.0944 0.4236 0.6065 5.750 1.0019 0.01511 0.00721 -0.0936 0.4106 0.6125 6.000 1.0245 0.01535 0.00751 -0.0927 0.3973 0.6187 6.250 1.0467 0.01563 0.00781 -0.0917 0.3835 0.6261 6.500 1.0681 0.01592 0.00814 -0.0906 0.3691 0.6328 6.750 1.0891 0.01623 0.00849 -0.0895 0.3541 0.6406 7.000 1.1094 0.01656 0.00886 -0.0883 0.3384 0.6481 7.250 1.1290 0.01692 0.00925 -0.0869 0.3218 0.6568 7.500 1.1477 0.01731 0.00967 -0.0854 0.3045 0.6659 7.750 1.1654 0.01774 0.01013 -0.0838 0.2864 0.6764 8.000 1.1814 0.01819 0.01062 -0.0819 0.2681 0.6871 8.250 1.1948 0.01869 0.01113 -0.0796 0.2496 0.6986 8.750 1.2195 0.01989 0.01235 -0.0748 0.2134 0.7256 9.000 1.2309 0.02056 0.01305 -0.0724 0.1964 0.7420 9.250 1.2414 0.02128 0.01379 -0.0699 0.1806 0.7615 9.500 1.2509 0.02202 0.01459 -0.0673 0.1662 0.7858 9.750 1.2585 0.02279 0.01543 -0.0644 0.1527 0.8184 10.000 1.2613 0.02345 0.01624 -0.0607 0.1413 0.8873 10.250 1.2675 0.02434 0.01715 -0.0581 0.1299 1.0000 10.500 1.2771 0.02542 0.01823 -0.0563 0.1184 1.0000 10.750 1.2858 0.02659 0.01941 -0.0546 0.1086 1.0000 11.000 1.2931 0.02790 0.02071 -0.0528 0.0998 1.0000 11.250 1.2999 0.02929 0.02211 -0.0512 0.0913 1.0000 11.500 1.3071 0.03072 0.02359 -0.0497 0.0839 1.0000 11.750 1.3114 0.03242 0.02530 -0.0482 0.0773 1.0000 12.000 1.3181 0.03401 0.02695 -0.0470 0.0709 1.0000 12.250 1.3212 0.03595 0.02892 -0.0458 0.0656 1.0000 12.500 1.3264 0.03780 0.03084 -0.0448 0.0605 1.0000 12.750 1.3276 0.04009 0.03314 -0.0439 0.0561 1.0000 13.000 1.3322 0.04214 0.03530 -0.0432 0.0520 1.0000 13.250 1.3331 0.04463 0.03784 -0.0427 0.0483 1.0000 13.500 1.3346 0.04716 0.04047 -0.0423 0.0453 1.0000 13.750 1.3360 0.04977 0.04317 -0.0420 0.0421 1.0000 14.000 1.3343 0.05283 0.04629 -0.0420 0.0398 1.0000 14.250 1.3346 0.05578 0.04935 -0.0421 0.0374 1.0000 14.500 1.3341 0.05892 0.05260 -0.0423 0.0352 1.0000 14.750 1.3312 0.06247 0.05622 -0.0429 0.0333 1.0000 15.000 1.3281 0.06617 0.06002 -0.0436 0.0318 1.0000 15.250 1.3267 0.06975 0.06373 -0.0443 0.0301 1.0000 15.500 1.3236 0.07368 0.06777 -0.0453 0.0286 1.0000 15.750 1.3183 0.07804 0.07222 -0.0467 0.0274 1.0000 16.000 1.3128 0.08256 0.07683 -0.0482 0.0263 1.0000 16.250 1.3097 0.08681 0.08124 -0.0496 0.0251 1.0000 16.500 1.3054 0.09133 0.08589 -0.0513 0.0240 1.0000 16.750 1.2998 0.09618 0.09085 -0.0533 0.0230 1.0000 17.000 1.2926 0.10139 0.09615 -0.0555 0.0223 1.0000