XFOIL Version 6.96 Calculated polar for: EPPLER EC 86(-3)-914 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 ------ -------- --------- --------- -------- -------- -------- -11.750 -0.3517 0.09628 0.09252 -0.0877 0.9662 0.0102 -11.500 -0.3788 0.08542 0.08157 -0.0943 0.9646 0.0100 -11.250 -0.3967 0.07654 0.07255 -0.1014 0.9630 0.0099 -11.000 -0.4118 0.06884 0.06468 -0.1084 0.9617 0.0098 -10.750 -0.4347 0.06504 0.06083 -0.1079 0.9577 0.0099 -10.500 -0.4530 0.06010 0.05573 -0.1106 0.9540 0.0097 -10.250 -0.4655 0.05592 0.05136 -0.1132 0.9514 0.0096 -10.000 -0.4773 0.05181 0.04702 -0.1158 0.9493 0.0095 -9.750 -0.5055 0.05055 0.04573 -0.1101 0.9428 0.0096 -9.500 -0.5199 0.04805 0.04303 -0.1089 0.9386 0.0094 -9.250 -0.5181 0.04453 0.03915 -0.1113 0.9362 0.0092 -9.000 -0.5320 0.04284 0.03730 -0.1076 0.9297 0.0092 -8.750 -0.5215 0.03996 0.03401 -0.1088 0.9265 0.0089 -8.500 -0.5011 0.03760 0.03134 -0.1102 0.9247 0.0088 -8.250 -0.4776 0.03550 0.02902 -0.1118 0.9235 0.0090 -8.000 -0.4646 0.03412 0.02755 -0.1109 0.9201 0.0095 -7.750 -0.4481 0.03280 0.02608 -0.1103 0.9168 0.0098 -7.500 -0.4237 0.03141 0.02452 -0.1109 0.9148 0.0100 -7.250 -0.3966 0.03007 0.02301 -0.1118 0.9133 0.0100 -7.000 -0.3675 0.02881 0.02163 -0.1129 0.9122 0.0099 -6.750 -0.3364 0.02763 0.02035 -0.1144 0.9112 0.0097 -6.500 -0.3093 0.02670 0.01933 -0.1152 0.9093 0.0096 -6.250 -0.2886 0.02590 0.01847 -0.1149 0.9053 0.0096 -6.000 -0.2566 0.02506 0.01754 -0.1168 0.9035 0.0095 -5.750 -0.2215 0.02427 0.01661 -0.1192 0.9021 0.0095 -5.500 -0.1855 0.02362 0.01584 -0.1216 0.9010 0.0095 -5.250 -0.1486 0.02306 0.01514 -0.1241 0.9000 0.0094 -5.000 -0.1117 0.02257 0.01452 -0.1264 0.8992 0.0095 -4.750 -0.0890 0.02233 0.01419 -0.1259 0.8948 0.0095 -4.500 -0.0577 0.02202 0.01378 -0.1270 0.8923 0.0096 -4.250 -0.0236 0.02173 0.01339 -0.1285 0.8905 0.0097 -4.000 0.0119 0.02145 0.01300 -0.1303 0.8891 0.0099 -3.750 0.0482 0.02120 0.01268 -0.1322 0.8880 0.0101 -3.500 0.0730 0.02112 0.01255 -0.1319 0.8837 0.0104 -3.250 0.1031 0.02097 0.01237 -0.1326 0.8804 0.0109 -3.000 0.1483 0.01996 0.01200 -0.1375 0.8796 0.1526 -2.750 0.1841 0.01978 0.01183 -0.1392 0.8779 0.1711 -2.500 0.2215 0.01955 0.01168 -0.1413 0.8766 0.1980 -2.250 0.2465 0.01950 0.01170 -0.1412 0.8711 0.2197 -2.000 0.2838 0.01912 0.01161 -0.1437 0.8683 0.2745 -1.750 0.3271 0.01858 0.01147 -0.1476 0.8667 0.3598 -1.500 0.3714 0.01794 0.01165 -0.1514 0.8655 0.5290 -1.250 0.3892 0.01814 0.01210 -0.1488 0.8589 0.5991 -1.000 0.4216 0.01806 0.01197 -0.1496 0.8551 0.6249 -0.750 0.4582 0.01783 0.01171 -0.1509 0.8527 0.6423 -0.500 0.4813 0.01784 0.01168 -0.1499 0.8439 0.6552 -0.250 0.5167 0.01746 0.01129 -0.1508 0.8403 0.6651 0.000 0.5380 0.01748 0.01130 -0.1494 0.8306 0.6726 0.250 0.5724 0.01712 0.01093 -0.1502 0.8268 0.6806 0.500 0.5922 0.01717 0.01099 -0.1485 0.8154 0.6867 0.750 0.6143 0.01713 0.01096 -0.1471 0.8041 0.6925 1.000 0.6439 0.01691 0.01072 -0.1472 0.7934 0.6990 1.250 0.6725 0.01658 0.01042 -0.1467 0.7838 0.7039 1.500 0.7026 0.01641 0.01022 -0.1468 0.7708 0.7126 1.750 0.7316 0.01610 0.00995 -0.1462 0.7579 0.7182 2.000 0.7713 0.01559 0.00941 -0.1479 0.7434 0.7255 2.250 0.8160 0.01494 0.00870 -0.1501 0.7243 0.7321 2.500 0.8579 0.01460 0.00827 -0.1521 0.6978 0.7390 2.750 0.8982 0.01451 0.00800 -0.1542 0.6650 0.7446 3.000 0.9261 0.01469 0.00801 -0.1540 0.6268 0.7466 3.250 0.9487 0.01506 0.00816 -0.1530 0.5854 0.7482 3.500 0.9671 0.01555 0.00844 -0.1513 0.5451 0.7502 3.750 0.9846 0.01608 0.00879 -0.1496 0.5077 0.7522 4.000 1.0028 0.01662 0.00916 -0.1481 0.4736 0.7540 4.250 1.0218 0.01718 0.00957 -0.1469 0.4418 0.7561 4.500 1.0417 0.01775 0.00999 -0.1459 0.4121 0.7583 4.750 1.0593 0.01830 0.01045 -0.1443 0.3854 0.7596 5.000 1.0771 0.01887 0.01092 -0.1428 0.3612 0.7607 5.250 1.0960 0.01940 0.01139 -0.1415 0.3395 0.7619 5.500 1.1152 0.01995 0.01188 -0.1403 0.3210 0.7633 5.750 1.1350 0.02048 0.01238 -0.1392 0.3053 0.7649 6.000 1.1556 0.02100 0.01291 -0.1383 0.2914 0.7666 6.250 1.1769 0.02153 0.01343 -0.1375 0.2790 0.7682 6.500 1.1983 0.02207 0.01398 -0.1368 0.2681 0.7697 6.750 1.2191 0.02267 0.01456 -0.1360 0.2579 0.7713 7.000 1.2415 0.02320 0.01514 -0.1355 0.2483 0.7728 7.250 1.2622 0.02379 0.01577 -0.1347 0.2408 0.7742 7.500 1.2823 0.02433 0.01639 -0.1337 0.2338 0.7754 7.750 1.3012 0.02494 0.01704 -0.1325 0.2252 0.7768 8.000 1.3186 0.02564 0.01773 -0.1312 0.2123 0.7783 8.250 1.3361 0.02636 0.01844 -0.1300 0.1993 0.7798 8.500 1.3559 0.02697 0.01916 -0.1291 0.1895 0.7813 8.750 1.3742 0.02768 0.01991 -0.1281 0.1772 0.7828 9.000 1.3904 0.02855 0.02073 -0.1269 0.1588 0.7844 9.250 1.4065 0.02951 0.02162 -0.1257 0.1337 0.7860 9.500 1.4061 0.03201 0.02347 -0.1227 0.0581 0.7875 10.000 1.4128 0.03646 0.02765 -0.1174 0.0099 0.7899 10.250 1.4225 0.03799 0.02930 -0.1155 0.0079 0.7913 10.500 1.4304 0.03971 0.03118 -0.1135 0.0065 0.7928 10.750 1.4399 0.04127 0.03292 -0.1117 0.0060 0.7945 11.000 1.4477 0.04303 0.03490 -0.1099 0.0057 0.7962 11.250 1.4539 0.04499 0.03705 -0.1081 0.0054 0.7978 11.500 1.4588 0.04713 0.03939 -0.1064 0.0052 0.7994 11.750 1.4614 0.04955 0.04199 -0.1047 0.0050 0.8010 12.000 1.4627 0.05221 0.04484 -0.1032 0.0048 0.8026 12.250 1.4616 0.05521 0.04803 -0.1018 0.0046 0.8042 12.500 1.4586 0.05846 0.05147 -0.1004 0.0045 0.8053 12.750 1.4538 0.06209 0.05530 -0.0994 0.0044 0.8066 13.000 1.4484 0.06600 0.05939 -0.0987 0.0043 0.8079 13.250 1.4409 0.07039 0.06397 -0.0984 0.0043 0.8093 13.500 1.4328 0.07511 0.06887 -0.0985 0.0042 0.8107 13.750 1.4224 0.08041 0.07436 -0.0992 0.0041 0.8121 14.000 1.4133 0.08577 0.07990 -0.1002 0.0041 0.8136 14.250 1.4026 0.09157 0.08588 -0.1017 0.0040 0.8151 14.500 1.3942 0.09724 0.09171 -0.1034 0.0040 0.8166