XFOIL Version 6.96 Calculated polar for: EPPLER 417 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 ------ -------- --------- --------- -------- -------- -------- -13.500 -0.5285 0.07987 0.07702 -0.0953 0.9813 0.0071 -13.250 -0.5488 0.07137 0.06838 -0.1013 0.9797 0.0071 -13.000 -0.5661 0.06438 0.06119 -0.1063 0.9782 0.0071 -12.750 -0.5818 0.05837 0.05499 -0.1104 0.9769 0.0071 -12.500 -0.5914 0.05349 0.04990 -0.1138 0.9757 0.0071 -12.250 -0.5944 0.04957 0.04579 -0.1168 0.9748 0.0070 -12.000 -0.6120 0.04610 0.04217 -0.1158 0.9707 0.0071 -11.750 -0.6191 0.04308 0.03901 -0.1161 0.9677 0.0072 -11.500 -0.6205 0.04005 0.03575 -0.1170 0.9656 0.0072 -11.250 -0.6111 0.03815 0.03377 -0.1185 0.9642 0.0074 -11.000 -0.6050 0.03529 0.03067 -0.1199 0.9629 0.0074 -10.750 -0.6125 0.03440 0.02973 -0.1162 0.9576 0.0076 -10.500 -0.6083 0.03285 0.02806 -0.1153 0.9544 0.0077 -10.250 -0.5983 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0.3871 0.00842 0.00345 -0.1352 0.8817 0.6029 -0.500 0.4099 0.00840 0.00343 -0.1341 0.8759 0.6053 -0.250 0.4374 0.00832 0.00333 -0.1341 0.8703 0.6079 0.000 0.4741 0.00817 0.00316 -0.1360 0.8671 0.6103 0.250 0.4963 0.00819 0.00322 -0.1349 0.8612 0.6121 0.500 0.5241 0.00815 0.00321 -0.1350 0.8559 0.6141 0.750 0.5628 0.00800 0.00307 -0.1373 0.8519 0.6162 1.000 0.5850 0.00799 0.00308 -0.1361 0.8408 0.6184 1.250 0.6150 0.00792 0.00300 -0.1366 0.8293 0.6206 1.500 0.6477 0.00786 0.00293 -0.1376 0.8179 0.6229 1.750 0.6808 0.00782 0.00287 -0.1388 0.8027 0.6253 2.000 0.7156 0.00781 0.00280 -0.1403 0.7806 0.6271 2.250 0.7464 0.00791 0.00280 -0.1409 0.7486 0.6289 2.500 0.7690 0.00815 0.00288 -0.1398 0.7082 0.6307 2.750 0.7853 0.00848 0.00303 -0.1373 0.6671 0.6327 3.000 0.7991 0.00887 0.00324 -0.1344 0.6259 0.6350 3.250 0.8119 0.00933 0.00349 -0.1314 0.5814 0.6374 3.500 0.8229 0.00990 0.00381 -0.1280 0.5271 0.6395 3.750 0.8343 0.01054 0.00416 -0.1249 0.4671 0.6415 4.000 0.8492 0.01111 0.00451 -0.1226 0.4150 0.6431 4.250 0.8643 0.01176 0.00490 -0.1204 0.3571 0.6449 4.500 0.8790 0.01252 0.00533 -0.1182 0.2887 0.6469 4.750 0.8949 0.01331 0.00579 -0.1164 0.2228 0.6491 5.000 0.9140 0.01391 0.00619 -0.1150 0.1791 0.6514 5.250 0.9336 0.01449 0.00659 -0.1138 0.1428 0.6535 5.500 0.9527 0.01512 0.00703 -0.1125 0.1052 0.6555 5.750 0.9715 0.01577 0.00752 -0.1112 0.0728 0.6573 6.000 0.9903 0.01639 0.00802 -0.1098 0.0459 0.6591 6.250 1.0071 0.01721 0.00867 -0.1082 0.0170 0.6612 6.500 1.0269 0.01777 0.00922 -0.1069 0.0120 0.6633 6.750 1.0479 0.01821 0.00972 -0.1059 0.0108 0.6656 7.000 1.0687 0.01868 0.01025 -0.1049 0.0101 0.6678 7.250 1.0888 0.01919 0.01081 -0.1037 0.0095 0.6699 7.500 1.1082 0.01977 0.01145 -0.1025 0.0090 0.6719 7.750 1.1266 0.02042 0.01218 -0.1011 0.0086 0.6738 8.000 1.1447 0.02107 0.01292 -0.0997 0.0083 0.6759 8.250 1.1630 0.02171 0.01365 -0.0983 0.0081 0.6782 8.500 1.1801 0.02243 0.01445 -0.0968 0.0079 0.6806 8.750 1.1967 0.02318 0.01528 -0.0952 0.0077 0.6829 9.000 1.2128 0.02397 0.01615 -0.0936 0.0075 0.6851 9.250 1.2282 0.02481 0.01705 -0.0919 0.0072 0.6872 9.500 1.2428 0.02568 0.01803 -0.0902 0.0070 0.6892 9.750 1.2569 0.02661 0.01904 -0.0884 0.0067 0.6914 10.000 1.2695 0.02765 0.02017 -0.0865 0.0066 0.6938 10.250 1.2814 0.02876 0.02137 -0.0846 0.0064 0.6964 10.500 1.2923 0.02998 0.02268 -0.0826 0.0063 0.6988 10.750 1.3017 0.03134 0.02412 -0.0805 0.0062 0.7012 11.000 1.3094 0.03288 0.02577 -0.0782 0.0061 0.7033 11.250 1.3157 0.03463 0.02765 -0.0760 0.0059 0.7053 11.500 1.3212 0.03655 0.02970 -0.0737 0.0058 0.7074 11.750 1.3305 0.03804 0.03131 -0.0720 0.0058 0.7099 12.000 1.3387 0.03967 0.03307 -0.0703 0.0058 0.7126 12.250 1.3462 0.04138 0.03493 -0.0686 0.0057 0.7154 12.750 1.3574 0.04529 0.03914 -0.0653 0.0056 0.7203 13.000 1.3614 0.04747 0.04148 -0.0637 0.0055 0.7228 13.250 1.3639 0.04986 0.04404 -0.0622 0.0055 0.7254 13.500 1.3650 0.05246 0.04683 -0.0609 0.0054 0.7280 13.750 1.3647 0.05532 0.04986 -0.0598 0.0053 0.7306 14.250 1.3596 0.06187 0.05678 -0.0582 0.0052 0.7358 14.500 1.3547 0.06563 0.06074 -0.0578 0.0052 0.7386 14.750 1.3482 0.06980 0.06511 -0.0579 0.0052 0.7415 15.000 1.3402 0.07438 0.06988 -0.0584 0.0051 0.7443 15.250 1.3307 0.07942 0.07513 -0.0595 0.0051 0.7470 15.500 1.3197 0.08495 0.08085 -0.0611 0.0051 0.7495 15.750 1.3074 0.09100 0.08711 -0.0634 0.0051 0.7518 16.000 1.2937 0.09765 0.09396 -0.0664 0.0051 0.7543 16.250 1.2792 0.10482 0.10133 -0.0700 0.0051 0.7567 16.500 1.2634 0.11257 0.10928 -0.0743 0.0051 0.7590 16.750 1.2472 0.12080 0.11770 -0.0792 0.0051 0.7612 17.000 1.2290 0.12993 0.12702 -0.0850 0.0051 0.7631 17.250 1.2112 0.13936 0.13663 -0.0912 0.0051 0.7650 17.500 1.1921 0.14962 0.14707 -0.0980 0.0052 0.7667 17.750 1.1705 0.16106 0.15868 -0.1057 0.0052 0.7681 18.000 1.1463 0.17400 0.17178 -0.1143 0.0053 0.7690