XFOIL Version 6.96 Calculated polar for: EPPLER 556 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 ------ -------- --------- --------- -------- -------- -------- -18.500 -0.5146 0.19988 0.19721 -0.0118 1.0000 0.0058 -17.500 -0.6778 0.13121 0.12814 -0.0368 1.0000 0.0044 -17.250 -0.7045 0.12113 0.11789 -0.0414 1.0000 0.0043 -17.000 -0.7251 0.11277 0.10941 -0.0454 1.0000 0.0044 -16.750 -0.7412 0.10562 0.10213 -0.0488 1.0000 0.0043 -16.500 -0.7558 0.09900 0.09538 -0.0519 1.0000 0.0043 -16.250 -0.7700 0.09267 0.08894 -0.0549 1.0000 0.0044 -16.000 -0.7792 0.08746 0.08362 -0.0573 1.0000 0.0043 -15.750 -0.7896 0.08222 0.07828 -0.0596 1.0000 0.0043 -15.500 -0.7977 0.07753 0.07348 -0.0616 1.0000 0.0043 -15.250 -0.8046 0.07319 0.06904 -0.0634 1.0000 0.0043 -15.000 -0.8126 0.06884 0.06459 -0.0651 1.0000 0.0044 -14.750 -0.8167 0.06519 0.06086 -0.0664 1.0000 0.0044 -14.500 -0.8213 0.06159 0.05718 -0.0676 1.0000 0.0045 -14.250 -0.8245 0.05836 0.05387 -0.0684 1.0000 0.0044 -14.000 -0.8276 0.05526 0.05070 -0.0692 1.0000 0.0046 -13.750 -0.8302 0.05238 0.04774 -0.0697 1.0000 0.0046 -13.500 -0.8331 0.04971 0.04499 -0.0699 1.0000 0.0046 -13.250 -0.8354 0.04725 0.04246 -0.0698 1.0000 0.0046 -13.000 -0.8378 0.04490 0.04006 -0.0696 1.0000 0.0048 -12.750 -0.8413 0.04260 0.03769 -0.0690 1.0000 0.0048 -12.500 -0.8454 0.04041 0.03544 -0.0682 1.0000 0.0049 -12.250 -0.8487 0.03847 0.03345 -0.0671 1.0000 0.0049 -12.000 -0.8492 0.03647 0.03139 -0.0667 0.9996 0.0049 -11.750 -0.8313 0.03422 0.02905 -0.0699 0.9972 0.0051 -11.500 -0.8123 0.03207 0.02680 -0.0732 0.9943 0.0052 -11.250 -0.7950 0.03012 0.02477 -0.0756 0.9903 0.0054 -11.000 -0.7762 0.02811 0.02268 -0.0785 0.9858 0.0055 -10.750 -0.7628 0.02629 0.02077 -0.0801 0.9785 0.0057 -10.500 -0.7430 0.02448 0.01888 -0.0826 0.9720 0.0058 -10.250 -0.7225 0.02240 0.01672 -0.0858 0.9640 0.0061 -10.000 -0.6980 0.02081 0.01504 -0.0886 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0.6107 0.4597 -0.250 0.4703 0.00887 0.00220 -0.1233 0.6016 0.4625 0.000 0.4980 0.00892 0.00224 -0.1233 0.5920 0.4654 0.250 0.5253 0.00899 0.00227 -0.1232 0.5829 0.4682 0.500 0.5526 0.00907 0.00231 -0.1230 0.5735 0.4710 0.750 0.5801 0.00914 0.00234 -0.1229 0.5643 0.4735 1.000 0.6070 0.00922 0.00240 -0.1227 0.5549 0.4761 1.250 0.6344 0.00928 0.00247 -0.1227 0.5454 0.4791 1.500 0.6614 0.00937 0.00254 -0.1225 0.5360 0.4823 1.750 0.6883 0.00947 0.00262 -0.1223 0.5263 0.4856 2.000 0.7153 0.00957 0.00270 -0.1221 0.5166 0.4885 2.250 0.7417 0.00968 0.00279 -0.1218 0.5066 0.4912 2.500 0.7683 0.00978 0.00289 -0.1216 0.4956 0.4941 2.750 0.7948 0.00990 0.00300 -0.1214 0.4848 0.4975 3.000 0.8208 0.01003 0.00312 -0.1210 0.4738 0.5012 3.250 0.8467 0.01019 0.00324 -0.1206 0.4623 0.5048 3.500 0.8729 0.01031 0.00338 -0.1203 0.4511 0.5081 3.750 0.8987 0.01046 0.00352 -0.1200 0.4404 0.5115 4.000 0.9240 0.01063 0.00368 -0.1195 0.4291 0.5153 4.250 0.9495 0.01079 0.00384 -0.1191 0.4171 0.5191 4.500 0.9747 0.01097 0.00401 -0.1187 0.4047 0.5229 4.750 0.9995 0.01116 0.00420 -0.1181 0.3921 0.5272 5.000 1.0240 0.01137 0.00440 -0.1176 0.3794 0.5318 5.250 1.0481 0.01160 0.00461 -0.1169 0.3669 0.5364 5.500 1.0721 0.01183 0.00484 -0.1163 0.3532 0.5406 5.750 1.0959 0.01207 0.00508 -0.1156 0.3395 0.5454 6.000 1.1191 0.01234 0.00533 -0.1148 0.3255 0.5506 6.250 1.1418 0.01263 0.00560 -0.1139 0.3105 0.5559 6.500 1.1636 0.01295 0.00591 -0.1129 0.2937 0.5618 6.750 1.1847 0.01331 0.00623 -0.1118 0.2767 0.5680 7.000 1.2053 0.01368 0.00658 -0.1107 0.2597 0.5737 7.250 1.2246 0.01408 0.00694 -0.1092 0.2410 0.5801 7.500 1.2421 0.01452 0.00734 -0.1075 0.2225 0.5867 7.750 1.2586 0.01499 0.00777 -0.1056 0.2044 0.5939 8.000 1.2747 0.01551 0.00824 -0.1037 0.1877 0.6020 8.250 1.2904 0.01605 0.00875 -0.1018 0.1717 0.6102 8.750 1.3209 0.01718 0.00984 -0.0978 0.1421 0.6280 9.250 1.3502 0.01835 0.01102 -0.0939 0.1187 0.6485 9.500 1.3643 0.01897 0.01167 -0.0920 0.1085 0.6606 9.750 1.3772 0.01965 0.01237 -0.0899 0.0991 0.6738 10.000 1.3887 0.02041 0.01316 -0.0877 0.0897 0.6882 10.250 1.4012 0.02113 0.01393 -0.0857 0.0817 0.7040 10.500 1.4122 0.02195 0.01480 -0.0836 0.0744 0.7214 10.750 1.4216 0.02288 0.01577 -0.0814 0.0669 0.7418 11.000 1.4325 0.02371 0.01671 -0.0795 0.0616 0.7686 11.250 1.4402 0.02472 0.01782 -0.0773 0.0561 0.8050 11.500 1.4444 0.02538 0.01877 -0.0741 0.0524 0.9340 11.750 1.4514 0.02658 0.01999 -0.0721 0.0478 1.0000 12.000 1.4601 0.02783 0.02128 -0.0705 0.0442 1.0000 12.250 1.4676 0.02922 0.02270 -0.0690 0.0404 1.0000 12.500 1.4742 0.03074 0.02425 -0.0675 0.0371 1.0000 12.750 1.4815 0.03226 0.02582 -0.0662 0.0344 1.0000 13.000 1.4862 0.03406 0.02765 -0.0649 0.0316 1.0000 13.250 1.4920 0.03584 0.02948 -0.0638 0.0293 1.0000 13.500 1.4970 0.03774 0.03144 -0.0628 0.0272 1.0000 13.750 1.4995 0.03995 0.03371 -0.0619 0.0251 1.0000 14.000 1.5039 0.04208 0.03591 -0.0612 0.0237 1.0000 14.250 1.5075 0.04435 0.03825 -0.0606 0.0223 1.0000 14.500 1.5090 0.04692 0.04088 -0.0601 0.0208 1.0000 14.750 1.5098 0.04966 0.04369 -0.0598 0.0195 1.0000 15.000 1.5120 0.05234 0.04647 -0.0596 0.0185 1.0000 15.250 1.5126 0.05529 0.04949 -0.0596 0.0173 1.0000 15.500 1.5117 0.05851 0.05279 -0.0598 0.0163 1.0000 15.750 1.5105 0.06190 0.05625 -0.0601 0.0153 1.0000 16.000 1.5104 0.06522 0.05968 -0.0606 0.0145 1.0000 16.250 1.5087 0.06886 0.06341 -0.0613 0.0137 1.0000 16.500 1.5055 0.07279 0.06743 -0.0621 0.0129 1.0000 16.750 1.5010 0.07703 0.07176 -0.0632 0.0122 1.0000 17.000 1.4988 0.08102 0.07586 -0.0643 0.0116 1.0000 17.250 1.4953 0.08530 0.08024 -0.0657 0.0111 1.0000 17.500 1.4906 0.08983 0.08487 -0.0672 0.0106 1.0000 17.750 1.4851 0.09458 0.08973 -0.0689 0.0101 1.0000 18.000 1.4786 0.09961 0.09485 -0.0708 0.0097 1.0000 18.250 1.4720 0.10471 0.10006 -0.0729 0.0093 1.0000 18.500 1.4666 0.10969 0.10515 -0.0751 0.0090 1.0000 18.750 1.4604 0.11484 0.11042 -0.0774 0.0087 1.0000 19.000 1.4538 0.12013 0.11582 -0.0799 0.0083 1.0000 19.250 1.4468 0.12555 0.12135 -0.0826 0.0080 1.0000