XFOIL Version 6.96 Calculated polar for: EPPLER 432 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.500 -0.4164 0.04062 0.03761 -0.1371 0.8195 0.0041 -12.250 -0.4448 0.03600 0.03268 -0.1374 0.7923 0.0041 -12.000 -0.4515 0.03379 0.03028 -0.1366 0.7739 0.0042 -11.750 -0.4724 0.03059 0.02681 -0.1347 0.7594 0.0041 -11.500 -0.4792 0.02867 0.02469 -0.1326 0.7472 0.0042 -11.250 -0.4856 0.02686 0.02267 -0.1300 0.7359 0.0042 -11.000 -0.4894 0.02538 0.02102 -0.1269 0.7266 0.0042 -10.500 -0.4827 0.02310 0.01839 -0.1217 0.7096 0.0042 -10.250 -0.4735 0.02187 0.01696 -0.1198 0.7020 0.0043 -10.000 -0.4594 0.02088 0.01582 -0.1184 0.6961 0.0043 -9.750 -0.4447 0.01982 0.01459 -0.1170 0.6899 0.0043 -9.500 -0.4276 0.01897 0.01358 -0.1158 0.6836 0.0043 -9.250 -0.4089 0.01813 0.01260 -0.1149 0.6783 0.0044 -9.000 -0.3886 0.01747 0.01182 -0.1141 0.6728 0.0044 -8.500 -0.3470 0.01603 0.01014 -0.1125 0.6638 0.0044 -8.250 -0.3247 0.01544 0.00945 -0.1119 0.6590 0.0045 -8.000 -0.3011 0.01503 0.00895 -0.1115 0.6544 0.0045 -7.750 -0.2774 0.01460 0.00843 -0.1110 0.6501 0.0046 -7.500 -0.2532 0.01415 0.00792 -0.1107 0.6464 0.0046 -7.250 -0.2309 0.01342 0.00710 -0.1100 0.6424 0.0048 -7.000 -0.2069 0.01295 0.00655 -0.1096 0.6384 0.0049 -6.750 -0.1824 0.01256 0.00609 -0.1092 0.6344 0.0050 -6.500 -0.1569 0.01218 0.00567 -0.1090 0.6312 0.0051 -6.250 -0.1312 0.01185 0.00529 -0.1088 0.6279 0.0052 -6.000 -0.1053 0.01155 0.00495 -0.1087 0.6243 0.0053 -5.750 -0.0794 0.01128 0.00462 -0.1085 0.6207 0.0054 -5.500 -0.0531 0.01102 0.00432 -0.1084 0.6174 0.0055 -5.250 -0.0262 0.01077 0.00404 -0.1084 0.6144 0.0058 -5.000 0.0008 0.01054 0.00378 -0.1083 0.6113 0.0060 -4.750 0.0278 0.01034 0.00355 -0.1083 0.6078 0.0063 -4.500 0.0548 0.01016 0.00333 -0.1083 0.6045 0.0067 -4.250 0.0820 0.00998 0.00312 -0.1083 0.6015 0.0075 -4.000 0.1097 0.00980 0.00293 -0.1084 0.5988 0.0092 -3.750 0.1375 0.00964 0.00277 -0.1086 0.5958 0.0112 -3.500 0.1651 0.00948 0.00262 -0.1087 0.5924 0.0159 -3.250 0.1926 0.00934 0.00249 -0.1088 0.5891 0.0239 -3.000 0.2202 0.00921 0.00238 -0.1089 0.5861 0.0343 -2.750 0.2484 0.00903 0.00227 -0.1092 0.5835 0.0515 -2.500 0.2763 0.00881 0.00217 -0.1095 0.5804 0.0840 -2.250 0.3042 0.00856 0.00208 -0.1098 0.5771 0.1303 -2.000 0.3320 0.00828 0.00199 -0.1102 0.5740 0.1966 -1.750 0.3598 0.00802 0.00191 -0.1106 0.5707 0.2649 -1.500 0.3885 0.00772 0.00184 -0.1111 0.5680 0.3450 -1.250 0.4175 0.00719 0.00173 -0.1120 0.5648 0.4876 -1.000 0.4466 0.00677 0.00172 -0.1127 0.5616 0.6291 -0.750 0.4752 0.00676 0.00175 -0.1130 0.5582 0.6638 -0.500 0.5035 0.00680 0.00178 -0.1132 0.5548 0.6812 -0.250 0.5325 0.00683 0.00181 -0.1135 0.5519 0.6949 0.000 0.5613 0.00687 0.00186 -0.1137 0.5487 0.7087 0.250 0.5897 0.00693 0.00193 -0.1139 0.5450 0.7242 0.500 0.6177 0.00700 0.00200 -0.1140 0.5413 0.7349 0.750 0.6460 0.00708 0.00204 -0.1142 0.5380 0.7402 1.000 0.6749 0.00712 0.00207 -0.1145 0.5347 0.7423 1.250 0.7035 0.00717 0.00209 -0.1148 0.5308 0.7441 1.500 0.7315 0.00723 0.00213 -0.1150 0.5268 0.7459 1.750 0.7592 0.00731 0.00218 -0.1151 0.5227 0.7478 2.000 0.7876 0.00735 0.00223 -0.1153 0.5187 0.7497 2.250 0.8156 0.00742 0.00229 -0.1155 0.5139 0.7515 2.500 0.8430 0.00751 0.00235 -0.1156 0.5089 0.7534 2.750 0.8709 0.00758 0.00241 -0.1158 0.5043 0.7552 3.000 0.8986 0.00766 0.00248 -0.1159 0.4987 0.7571 3.250 0.9256 0.00777 0.00256 -0.1160 0.4931 0.7591 3.500 0.9532 0.00786 0.00264 -0.1161 0.4878 0.7609 3.750 0.9802 0.00794 0.00272 -0.1161 0.4817 0.7627 4.000 1.0065 0.00806 0.00283 -0.1160 0.4757 0.7645 4.250 1.0336 0.00815 0.00293 -0.1161 0.4696 0.7663 4.500 1.0595 0.00829 0.00305 -0.1159 0.4627 0.7682 4.750 1.0860 0.00840 0.00316 -0.1159 0.4561 0.7702 5.000 1.1116 0.00855 0.00330 -0.1157 0.4482 0.7722 5.250 1.1373 0.00869 0.00343 -0.1155 0.4408 0.7744 5.500 1.1621 0.00887 0.00358 -0.1152 0.4320 0.7765 5.750 1.1873 0.00902 0.00374 -0.1150 0.4236 0.7784 6.000 1.2107 0.00923 0.00392 -0.1144 0.4134 0.7804 6.250 1.2344 0.00942 0.00411 -0.1139 0.4027 0.7825 6.500 1.2574 0.00964 0.00431 -0.1132 0.3918 0.7846 6.750 1.2788 0.00992 0.00455 -0.1123 0.3782 0.7869 7.000 1.2993 0.01021 0.00480 -0.1112 0.3643 0.7893 7.250 1.3175 0.01054 0.00508 -0.1097 0.3486 0.7917 7.500 1.3338 0.01088 0.00537 -0.1078 0.3334 0.7941 7.750 1.3483 0.01128 0.00572 -0.1056 0.3166 0.7969 8.000 1.3619 0.01173 0.00612 -0.1033 0.2994 0.7998 8.250 1.3752 0.01221 0.00654 -0.1010 0.2835 0.8028 8.500 1.3870 0.01274 0.00702 -0.0986 0.2669 0.8059 8.750 1.3976 0.01334 0.00755 -0.0960 0.2501 0.8089 9.000 1.4081 0.01394 0.00811 -0.0934 0.2352 0.8118 9.250 1.4180 0.01458 0.00872 -0.0909 0.2210 0.8151 9.500 1.4269 0.01529 0.00940 -0.0883 0.2072 0.8189 9.750 1.4351 0.01608 0.01015 -0.0858 0.1938 0.8230 10.250 1.4484 0.01793 0.01194 -0.0807 0.1679 0.8314 10.500 1.4560 0.01889 0.01291 -0.0785 0.1587 0.8360 10.750 1.4603 0.02010 0.01410 -0.0761 0.1464 0.8409 11.000 1.4659 0.02131 0.01530 -0.0739 0.1358 0.8458 11.250 1.4684 0.02278 0.01675 -0.0717 0.1234 0.8518 11.500 1.4731 0.02419 0.01817 -0.0698 0.1140 0.8581 11.750 1.4776 0.02567 0.01967 -0.0680 0.1063 0.8657 12.250 1.4826 0.02907 0.02310 -0.0645 0.0878 0.8854 12.500 1.4812 0.03110 0.02514 -0.0626 0.0771 0.9002 12.750 1.4822 0.03282 0.02695 -0.0607 0.0710 0.9316 13.250 1.4910 0.03672 0.03091 -0.0591 0.0587 1.0000 13.500 1.4858 0.03959 0.03371 -0.0579 0.0469 1.0000 13.750 1.4911 0.04157 0.03573 -0.0573 0.0441 1.0000 14.000 1.4930 0.04394 0.03809 -0.0566 0.0389 1.0000 14.250 1.4973 0.04612 0.04030 -0.0561 0.0353 1.0000 14.500 1.4996 0.04856 0.04275 -0.0556 0.0318 1.0000 14.750 1.5031 0.05093 0.04516 -0.0552 0.0286 1.0000 15.000 1.5054 0.05347 0.04772 -0.0549 0.0253 1.0000 15.250 1.5088 0.05596 0.05026 -0.0548 0.0232 1.0000 15.500 1.5114 0.05859 0.05292 -0.0547 0.0210 1.0000 15.750 1.5148 0.06115 0.05552 -0.0547 0.0190 1.0000 16.000 1.5165 0.06399 0.05840 -0.0547 0.0173 1.0000 16.250 1.5180 0.06690 0.06134 -0.0549 0.0150 1.0000 16.500 1.5211 0.06967 0.06417 -0.0551 0.0143 1.0000 16.750 1.5224 0.07270 0.06725 -0.0554 0.0126 1.0000 17.000 1.5238 0.07576 0.07037 -0.0558 0.0115 1.0000 17.250 1.5252 0.07889 0.07356 -0.0563 0.0105 1.0000 17.500 1.5253 0.08224 0.07696 -0.0569 0.0093 1.0000 17.750 1.5263 0.08552 0.08030 -0.0576 0.0086 1.0000 18.000 1.5254 0.08909 0.08393 -0.0584 0.0075 1.0000 18.250 1.5260 0.09247 0.08738 -0.0592 0.0070 1.0000 18.500 1.5256 0.09609 0.09107 -0.0602 0.0063 1.0000 18.750 1.5250 0.09975 0.09479 -0.0612 0.0058 1.0000 19.000 1.5239 0.10353 0.09865 -0.0624 0.0053 1.0000