XFOIL Version 6.96 Calculated polar for: EPPLER 1233 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.500 -0.6270 0.10504 0.10177 -0.0566 1.0000 0.0095 -16.250 -0.6655 0.09408 0.09064 -0.0622 1.0000 0.0095 -16.000 -0.6985 0.08450 0.08089 -0.0672 1.0000 0.0095 -15.750 -0.7217 0.07688 0.07313 -0.0712 1.0000 0.0094 -15.500 -0.7465 0.06935 0.06545 -0.0752 1.0000 0.0093 -15.250 -0.7616 0.06366 0.05962 -0.0781 1.0000 0.0093 -15.000 -0.7784 0.05824 0.05406 -0.0805 1.0000 0.0094 -14.750 -0.7912 0.05392 0.04961 -0.0819 1.0000 0.0095 -14.500 -0.8033 0.05014 0.04571 -0.0827 1.0000 0.0095 -14.250 -0.7992 0.04625 0.04167 -0.0863 0.9983 0.0096 -14.000 -0.7911 0.04313 0.03843 -0.0894 0.9963 0.0096 -13.750 -0.7804 0.04035 0.03551 -0.0923 0.9943 0.0097 -13.500 -0.7699 0.03787 0.03290 -0.0944 0.9923 0.0098 -13.250 -0.7586 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0.0152 -8.500 -0.3023 0.01555 0.00854 -0.1185 0.7330 0.0161 -8.250 -0.2857 0.01529 0.00819 -0.1167 0.7152 0.0168 -8.000 -0.2684 0.01505 0.00783 -0.1149 0.6983 0.0177 -7.750 -0.2508 0.01480 0.00748 -0.1132 0.6824 0.0188 -7.500 -0.2318 0.01452 0.00715 -0.1117 0.6681 0.0199 -7.250 -0.2120 0.01429 0.00683 -0.1104 0.6550 0.0214 -7.000 -0.1927 0.01403 0.00651 -0.1089 0.6413 0.0234 -6.750 -0.1720 0.01381 0.00623 -0.1077 0.6286 0.0255 -6.500 -0.1507 0.01357 0.00595 -0.1066 0.6176 0.0289 -6.000 -0.1074 0.01310 0.00544 -0.1046 0.5960 0.0405 -5.750 -0.0853 0.01292 0.00522 -0.1036 0.5852 0.0479 -5.500 -0.0623 0.01273 0.00502 -0.1028 0.5746 0.0562 -5.250 -0.0391 0.01256 0.00484 -0.1020 0.5652 0.0643 -5.000 -0.0152 0.01240 0.00466 -0.1013 0.5557 0.0727 -4.750 0.0086 0.01226 0.00450 -0.1007 0.5466 0.0809 -4.500 0.0331 0.01212 0.00434 -0.1001 0.5372 0.0902 -4.000 0.0819 0.01181 0.00405 -0.0990 0.5202 0.1168 -3.500 0.1311 0.01143 0.00378 -0.0981 0.5045 0.1631 -3.250 0.1556 0.01125 0.00365 -0.0976 0.4963 0.1925 -3.000 0.1807 0.01102 0.00352 -0.0973 0.4891 0.2322 -2.750 0.2059 0.01074 0.00339 -0.0971 0.4820 0.2842 -2.500 0.2305 0.01044 0.00326 -0.0968 0.4754 0.3491 -2.250 0.2564 0.01005 0.00313 -0.0969 0.4692 0.4307 -2.000 0.2821 0.00978 0.00309 -0.0967 0.4623 0.5116 -1.750 0.3079 0.00973 0.00311 -0.0963 0.4557 0.5569 -1.500 0.3348 0.00972 0.00314 -0.0961 0.4495 0.5861 -1.250 0.3612 0.00977 0.00319 -0.0958 0.4436 0.6068 -1.000 0.3874 0.00985 0.00324 -0.0954 0.4383 0.6233 -0.750 0.4144 0.00991 0.00330 -0.0952 0.4331 0.6371 -0.500 0.4407 0.01001 0.00337 -0.0948 0.4273 0.6495 0.000 0.4927 0.01026 0.00355 -0.0940 0.4168 0.6785 0.250 0.5182 0.01037 0.00367 -0.0934 0.4119 0.6881 0.500 0.5437 0.01050 0.00374 -0.0929 0.4071 0.6954 0.750 0.5689 0.01061 0.00380 -0.0924 0.4028 0.6996 1.000 0.5949 0.01068 0.00386 -0.0920 0.3987 0.7026 1.250 0.6204 0.01077 0.00393 -0.0916 0.3942 0.7056 1.500 0.6453 0.01089 0.00400 -0.0910 0.3894 0.7089 1.750 0.6699 0.01103 0.00408 -0.0904 0.3851 0.7122 2.000 0.6960 0.01112 0.00415 -0.0901 0.3815 0.7153 2.250 0.7214 0.01122 0.00422 -0.0897 0.3776 0.7180 2.500 0.7458 0.01134 0.00433 -0.0891 0.3738 0.7206 2.750 0.7695 0.01149 0.00445 -0.0884 0.3699 0.7234 3.000 0.7943 0.01162 0.00457 -0.0879 0.3663 0.7260 3.250 0.8196 0.01174 0.00468 -0.0874 0.3627 0.7289 3.500 0.8442 0.01188 0.00481 -0.0869 0.3590 0.7320 3.750 0.8684 0.01205 0.00494 -0.0864 0.3555 0.7348 4.000 0.8918 0.01223 0.00509 -0.0857 0.3522 0.7372 4.250 0.9159 0.01236 0.00524 -0.0851 0.3494 0.7395 4.500 0.9402 0.01249 0.00540 -0.0845 0.3461 0.7420 4.750 0.9638 0.01265 0.00556 -0.0838 0.3426 0.7449 5.000 0.9867 0.01284 0.00574 -0.0831 0.3392 0.7478 5.250 1.0092 0.01304 0.00592 -0.0823 0.3362 0.7506 5.500 1.0322 0.01324 0.00612 -0.0816 0.3335 0.7531 6.000 1.0792 0.01357 0.00649 -0.0804 0.3280 0.7580 6.250 1.1012 0.01376 0.00671 -0.0795 0.3247 0.7608 6.500 1.1223 0.01399 0.00694 -0.0785 0.3215 0.7637 6.750 1.1430 0.01424 0.00719 -0.0775 0.3187 0.7665 7.000 1.1651 0.01446 0.00743 -0.0767 0.3164 0.7692 7.250 1.1877 0.01467 0.00767 -0.0760 0.3141 0.7721 7.500 1.2093 0.01489 0.00793 -0.0752 0.3112 0.7749 7.750 1.2297 0.01513 0.00821 -0.0742 0.3085 0.7778 8.000 1.2491 0.01541 0.00851 -0.0730 0.3054 0.7808 8.250 1.2679 0.01573 0.00884 -0.0718 0.3027 0.7838 8.500 1.2874 0.01603 0.00917 -0.0707 0.3005 0.7871 8.750 1.3083 0.01630 0.00949 -0.0699 0.2984 0.7905 9.000 1.3283 0.01659 0.00983 -0.0689 0.2958 0.7938 9.250 1.3468 0.01690 0.01020 -0.0678 0.2932 0.7971 9.500 1.3643 0.01727 0.01061 -0.0665 0.2904 0.8006 9.750 1.3807 0.01770 0.01105 -0.0651 0.2877 0.8044 10.000 1.3966 0.01816 0.01154 -0.0637 0.2853 0.8087 10.250 1.4155 0.01851 0.01197 -0.0627 0.2834 0.8128 10.500 1.4330 0.01890 0.01244 -0.0616 0.2810 0.8174 10.750 1.4496 0.01934 0.01295 -0.0604 0.2783 0.8223 11.000 1.4648 0.01986 0.01352 -0.0590 0.2756 0.8274 11.250 1.4788 0.02043 0.01414 -0.0576 0.2730 0.8330 11.500 1.4910 0.02109 0.01485 -0.0560 0.2704 0.8400 11.750 1.5062 0.02165 0.01549 -0.0548 0.2679 0.8476 12.000 1.5205 0.02221 0.01616 -0.0535 0.2650 0.8565 12.250 1.5329 0.02289 0.01692 -0.0520 0.2617 0.8671 12.750 1.5501 0.02458 0.01878 -0.0484 0.2550 0.9110 13.250 1.5804 0.02618 0.02058 -0.0474 0.2488 1.0000 13.500 1.5909 0.02726 0.02170 -0.0464 0.2452 1.0000 13.750 1.5988 0.02855 0.02301 -0.0453 0.2419 1.0000 14.000 1.6066 0.02989 0.02439 -0.0443 0.2388 1.0000 14.250 1.6179 0.03103 0.02561 -0.0436 0.2351 1.0000 14.500 1.6245 0.03254 0.02717 -0.0427 0.2303 1.0000 14.750 1.6264 0.03446 0.02911 -0.0417 0.2258 1.0000 15.000 1.6324 0.03616 0.03087 -0.0410 0.2207 1.0000 15.250 1.6316 0.03847 0.03320 -0.0402 0.2135 1.0000 15.500 1.6311 0.04083 0.03560 -0.0395 0.2082 1.0000 15.750 1.6322 0.04314 0.03797 -0.0390 0.2024 1.0000 16.000 1.6246 0.04636 0.04120 -0.0385 0.1964 1.0000 16.250 1.6246 0.04893 0.04384 -0.0383 0.1903 1.0000 16.500 1.6172 0.05233 0.04728 -0.0381 0.1845 1.0000 16.750 1.6118 0.05563 0.05064 -0.0381 0.1789 1.0000 17.000 1.6019 0.05953 0.05458 -0.0383 0.1721 1.0000 17.250 1.5929 0.06341 0.05852 -0.0386 0.1671 1.0000 17.500 1.5835 0.06746 0.06262 -0.0391 0.1608 1.0000 17.750 1.5685 0.07229 0.06749 -0.0398 0.1547 1.0000 18.000 1.5572 0.07677 0.07204 -0.0406 0.1484 1.0000 18.250 1.5411 0.08199 0.07730 -0.0418 0.1428 1.0000 18.500 1.5267 0.08709 0.08245 -0.0430 0.1359 1.0000