XFOIL Version 6.96 Calculated polar for: EPPLER 546 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.250 -0.3330 0.12005 0.11546 -0.0466 1.0000 0.1165 -12.000 -0.3050 0.11758 0.11297 -0.0436 1.0000 0.1210 -11.750 -0.4473 0.11622 0.11134 -0.0479 1.0000 0.1163 -11.500 -0.4154 0.11401 0.10909 -0.0434 1.0000 0.1197 -11.250 -0.4124 0.11065 0.10576 -0.0436 1.0000 0.1242 -11.000 -0.4816 0.10283 0.09814 -0.0547 1.0000 0.1301 -10.750 -0.4339 0.10131 0.09659 -0.0476 1.0000 0.1337 -10.500 -0.4282 0.09824 0.09355 -0.0470 1.0000 0.1381 -10.250 -0.4973 0.09056 0.08601 -0.0555 1.0000 0.1447 -10.000 -0.4652 0.08772 0.08323 -0.0518 1.0000 0.1496 -7.500 -0.7390 0.04817 0.04141 -0.0197 0.9912 0.0518 -7.250 -0.7141 0.04284 0.03507 -0.0201 0.9839 0.0455 -7.000 -0.6812 0.04007 0.03185 -0.0214 0.9765 0.0446 -6.750 -0.6438 0.03673 0.02823 -0.0240 0.9713 0.0462 -6.500 -0.6099 0.03466 0.02606 -0.0255 0.9638 0.0481 -6.250 -0.5657 0.03239 0.02353 -0.0280 0.9590 0.0502 -6.000 -0.5265 0.03067 0.02159 -0.0294 0.9525 0.0526 -5.750 -0.4858 0.02891 0.01995 -0.0316 0.9468 0.0600 -5.500 -0.4462 0.02730 0.01845 -0.0336 0.9416 0.0729 -5.250 -0.4241 0.02584 0.01722 -0.0332 0.9317 0.0935 -5.000 -0.4127 0.02375 0.01583 -0.0312 0.9218 0.1694 -4.750 -0.4169 0.02350 0.01825 -0.0228 0.9122 0.6561 -4.500 -0.3903 0.02709 0.02166 -0.0170 0.9019 0.7086 -4.250 -0.2503 0.03351 0.02760 -0.0233 0.9122 0.7588 -4.000 -0.0965 0.03548 0.02908 -0.0382 0.9207 0.7984 -3.750 -0.0240 0.03510 0.02845 -0.0450 0.9184 0.8244 -3.500 0.0444 0.03416 0.02728 -0.0524 0.9153 0.8420 -3.250 0.1113 0.03307 0.02600 -0.0598 0.9122 0.8601 -3.000 0.1594 0.03226 0.02506 -0.0640 0.9028 0.8775 -2.750 0.2116 0.03153 0.02419 -0.0691 0.8966 0.8980 -0.750 0.4254 0.02800 0.02002 -0.0752 0.8108 0.9278 -0.500 0.4439 0.02774 0.01973 -0.0744 0.8008 0.9264 -0.250 0.4585 0.02767 0.01964 -0.0728 0.7909 0.9252 0.000 0.4779 0.02746 0.01938 -0.0720 0.7828 0.9244 0.250 0.4884 0.02754 0.01948 -0.0697 0.7727 0.9234 0.500 0.5086 0.02734 0.01922 -0.0690 0.7658 0.9228 0.750 0.5163 0.02754 0.01946 -0.0662 0.7558 0.9221 1.000 0.5372 0.02733 0.01920 -0.0655 0.7494 0.9219 1.250 0.5418 0.02762 0.01955 -0.0622 0.7396 0.9208 1.500 0.5637 0.02743 0.01934 -0.0616 0.7335 0.9215 1.750 0.5657 0.02777 0.01974 -0.0579 0.7240 0.9201 2.000 0.5870 0.02759 0.01954 -0.0572 0.7179 0.9208 2.250 0.5903 0.02795 0.01997 -0.0537 0.7089 0.9207 2.500 0.6074 0.02783 0.01984 -0.0522 0.7026 0.9205 2.750 0.6111 0.02818 0.02028 -0.0487 0.6943 0.9209 3.000 0.6276 0.02811 0.02024 -0.0472 0.6875 0.9218 3.250 0.6324 0.02836 0.02053 -0.0437 0.6799 0.9219 3.500 0.6402 0.02846 0.02068 -0.0407 0.6724 0.9222 3.750 0.6562 0.02842 0.02067 -0.0389 0.6662 0.9236 4.000 0.6474 0.02887 0.02119 -0.0332 0.6573 0.9249 4.250 0.6770 0.02838 0.02070 -0.0334 0.6524 0.9257 4.500 0.6116 0.02948 0.02187 -0.0181 0.6423 0.9283 4.750 0.6704 0.02874 0.02116 -0.0233 0.6371 0.9291 5.000 0.6620 0.02941 0.02197 -0.0182 0.6267 0.9317 5.250 0.7128 0.02867 0.02125 -0.0219 0.6212 0.9326 5.500 0.6868 0.02947 0.02215 -0.0137 0.6111 0.9359 5.750 0.7385 0.02861 0.02134 -0.0173 0.6052 0.9368 6.000 0.6994 0.02949 0.02231 -0.0069 0.5953 0.9423 6.250 0.7607 0.02840 0.02126 -0.0118 0.5891 0.9431 6.500 0.7712 0.02880 0.02182 -0.0098 0.5778 0.9462 6.750 0.8110 0.02826 0.02136 -0.0117 0.5688 0.9479 7.000 0.8464 0.02771 0.02090 -0.0128 0.5586 0.9500 7.250 0.8535 0.02781 0.02112 -0.0097 0.5476 0.9541 7.500 0.8888 0.02712 0.02049 -0.0105 0.5377 0.9566 7.750 0.9344 0.02638 0.01981 -0.0132 0.5250 0.9583 8.000 0.9644 0.02608 0.01966 -0.0138 0.5103 0.9614 8.250 0.9943 0.02568 0.01936 -0.0142 0.4947 0.9651 8.500 1.0156 0.02530 0.01907 -0.0131 0.4790 0.9698 8.750 1.0468 0.02492 0.01880 -0.0139 0.4598 0.9730 9.000 1.0658 0.02479 0.01883 -0.0129 0.4390 0.9782 9.250 1.0878 0.02452 0.01859 -0.0123 0.4163 0.9836 9.500 1.1037 0.02465 0.01883 -0.0112 0.3897 0.9909 9.750 1.1121 0.02485 0.01906 -0.0090 0.3634 1.0000 10.000 1.0854 0.02475 0.01889 -0.0003 0.3538 1.0000 10.250 1.0739 0.02510 0.01921 0.0049 0.3348 1.0000 10.500 1.0732 0.02591 0.01991 0.0077 0.3085 1.0000 10.750 1.0730 0.02717 0.02106 0.0098 0.2806 1.0000 11.000 1.0728 0.02875 0.02250 0.0115 0.2536 1.0000 11.250 1.0724 0.03057 0.02413 0.0129 0.2286 1.0000 11.500 1.0710 0.03261 0.02606 0.0141 0.2052 1.0000 11.750 1.0703 0.03477 0.02805 0.0152 0.1841 1.0000 12.000 1.0694 0.03705 0.03027 0.0161 0.1647 1.0000 12.250 1.0697 0.03935 0.03247 0.0169 0.1478 1.0000 12.500 1.0710 0.04168 0.03469 0.0175 0.1326 1.0000 12.750 1.0739 0.04400 0.03694 0.0181 0.1190 1.0000 13.000 1.0783 0.04631 0.03923 0.0187 0.1071 1.0000 13.250 1.0846 0.04861 0.04152 0.0192 0.0966 1.0000 13.500 1.0940 0.05081 0.04365 0.0196 0.0873 1.0000 13.750 1.1023 0.05298 0.04578 0.0199 0.0795 1.0000 14.000 1.1070 0.05568 0.04868 0.0202 0.0731 1.0000 14.250 1.1220 0.05784 0.05069 0.0205 0.0662 1.0000 14.500 1.1185 0.06100 0.05417 0.0206 0.0623 1.0000 14.750 1.1349 0.06327 0.05627 0.0207 0.0565 1.0000 15.000 1.1246 0.06704 0.06042 0.0206 0.0542 1.0000 15.250 1.1213 0.07049 0.06407 0.0203 0.0514 1.0000 15.500 1.1295 0.07343 0.06692 0.0201 0.0473 1.0000 15.750 1.1155 0.07800 0.07184 0.0192 0.0464 1.0000 16.000 1.1000 0.08310 0.07726 0.0178 0.0453 1.0000 16.250 1.0852 0.08846 0.08289 0.0162 0.0446 1.0000 16.500 1.0695 0.09402 0.08868 0.0140 0.0435 1.0000 16.750 1.0504 0.10040 0.09530 0.0112 0.0433 1.0000 17.000 1.0230 0.10846 0.10365 0.0070 0.0440 1.0000 17.250 0.9927 0.11769 0.11313 0.0018 0.0450 1.0000 17.500 0.9638 0.12733 0.12296 -0.0041 0.0459 1.0000 17.750 0.9373 0.13732 0.13307 -0.0102 0.0469 1.0000 18.000 0.9127 0.14775 0.14357 -0.0165 0.0477 1.0000 18.250 0.8161 0.18800 0.18365 -0.0369 0.0667 1.0000