EPPLER 328 AIRFOIL (e328-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 328 AIRFOIL (e328-il) Reynolds number: 100,000 Max Cl/Cd: 37.68 at α=12.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e328-il-100000.txt Download as CSV file: xf-e328-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 328 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2888 0.11243 0.10793 -0.0262 1.0000 0.0814
-10.500 -0.2997 0.10943 0.10497 -0.0291 1.0000 0.0821
-10.250 -0.3160 0.10619 0.10180 -0.0327 1.0000 0.0826
-10.000 -0.2782 0.10120 0.09682 -0.0273 1.0000 0.0879
-9.750 -0.2766 0.09781 0.09347 -0.0279 1.0000 0.0908
-9.500 -0.2846 0.09414 0.08986 -0.0299 1.0000 0.0947
-9.250 -0.3016 0.09037 0.08616 -0.0333 1.0000 0.0963
-9.000 -0.3794 0.09414 0.08958 -0.0296 1.0000 0.0876
-8.750 -0.3803 0.09070 0.08620 -0.0306 1.0000 0.0919
-8.500 -0.3913 0.08661 0.08219 -0.0339 1.0000 0.0937
-8.250 -0.4091 0.08299 0.07862 -0.0357 1.0000 0.0948
-8.000 -0.4365 0.08072 0.07637 -0.0345 1.0000 0.0958
-7.750 -0.4624 0.07897 0.07455 -0.0326 1.0000 0.0967
-7.500 -0.4655 0.07415 0.06984 -0.0311 1.0000 0.0995
-7.250 -0.4661 0.07127 0.06699 -0.0293 1.0000 0.1002
-7.000 -0.4602 0.06877 0.06460 -0.0270 1.0000 0.1067
-6.750 -0.4804 0.06759 0.06335 -0.0233 1.0000 0.1107
-6.500 -0.5075 0.06751 0.06325 -0.0175 1.0000 0.1115
-6.250 -0.4968 0.06278 0.05855 -0.0191 0.9927 0.1159
-6.000 -0.4663 0.05859 0.05404 -0.0243 0.9766 0.1304
-5.750 -0.4338 0.05459 0.04983 -0.0285 0.9617 0.1460
-5.500 -0.4003 0.05014 0.04536 -0.0319 0.9478 0.1634
-5.250 -0.3653 0.04632 0.04153 -0.0349 0.9341 0.1842
-5.000 -0.3355 0.04302 0.03815 -0.0369 0.9187 0.2175
-4.500 -0.2392 0.03228 0.02473 -0.0374 0.8880 0.0669
-4.250 -0.2022 0.02925 0.02092 -0.0371 0.8709 0.0576
-4.000 -0.1664 0.02698 0.01833 -0.0376 0.8529 0.0560
-3.750 -0.1361 0.02538 0.01638 -0.0370 0.8327 0.0573
-3.500 -0.1053 0.02352 0.01447 -0.0371 0.8137 0.0613
-3.250 -0.0742 0.02221 0.01301 -0.0367 0.7957 0.0644
-3.000 -0.0448 0.02118 0.01181 -0.0359 0.7788 0.0697
-2.750 -0.0199 0.02010 0.01077 -0.0347 0.7627 0.0832
-2.500 0.2697 0.01863 0.01153 -0.0693 0.7373 1.0000
-2.250 0.2898 0.01857 0.01122 -0.0683 0.7211 1.0000
-2.000 0.3101 0.01853 0.01095 -0.0674 0.7060 1.0000
-1.750 0.3304 0.01852 0.01073 -0.0664 0.6921 1.0000
-1.500 0.3507 0.01852 0.01056 -0.0655 0.6784 1.0000
-1.250 0.3714 0.01855 0.01044 -0.0646 0.6660 1.0000
-1.000 0.3924 0.01860 0.01032 -0.0637 0.6550 1.0000
-0.750 0.4134 0.01865 0.01021 -0.0628 0.6441 1.0000
-0.500 0.4344 0.01874 0.01020 -0.0620 0.6331 1.0000
-0.250 0.4559 0.01884 0.01016 -0.0611 0.6241 1.0000
0.000 0.4772 0.01895 0.01018 -0.0603 0.6140 1.0000
0.250 0.4986 0.01910 0.01024 -0.0594 0.6051 1.0000
0.500 0.5203 0.01923 0.01027 -0.0586 0.5967 1.0000
0.750 0.5417 0.01942 0.01043 -0.0578 0.5880 1.0000
1.000 0.5635 0.01957 0.01047 -0.0570 0.5804 1.0000
1.250 0.5847 0.01981 0.01071 -0.0562 0.5722 1.0000
1.500 0.6067 0.01999 0.01082 -0.0554 0.5651 1.0000
1.750 0.6279 0.02026 0.01108 -0.0545 0.5577 1.0000
2.000 0.6495 0.02048 0.01128 -0.0537 0.5504 1.0000
2.250 0.6712 0.02075 0.01150 -0.0528 0.5441 1.0000
2.500 0.6918 0.02107 0.01187 -0.0519 0.5366 1.0000
2.750 0.7145 0.02127 0.01197 -0.0511 0.5310 1.0000
3.000 0.7338 0.02170 0.01253 -0.0501 0.5235 1.0000
3.250 0.7556 0.02195 0.01275 -0.0493 0.5174 1.0000
3.500 0.7761 0.02234 0.01317 -0.0483 0.5113 1.0000
3.750 0.7958 0.02273 0.01363 -0.0472 0.5044 1.0000
4.000 0.8187 0.02296 0.01381 -0.0464 0.4994 1.0000
4.250 0.8357 0.02356 0.01458 -0.0451 0.4922 1.0000
4.500 0.8565 0.02387 0.01489 -0.0441 0.4863 1.0000
4.750 0.8767 0.02430 0.01534 -0.0430 0.4809 1.0000
5.000 0.8931 0.02490 0.01610 -0.0415 0.4738 1.0000
5.250 0.9153 0.02513 0.01630 -0.0406 0.4687 1.0000
5.500 0.9297 0.02590 0.01723 -0.0388 0.4620 1.0000
5.750 0.9483 0.02632 0.01772 -0.0375 0.4558 1.0000
6.000 0.9709 0.02656 0.01792 -0.0365 0.4509 1.0000
6.250 0.9801 0.02752 0.01913 -0.0341 0.4433 1.0000
6.500 1.0020 0.02769 0.01928 -0.0331 0.4379 1.0000
6.750 1.0131 0.02854 0.02032 -0.0308 0.4313 1.0000
7.000 1.0292 0.02899 0.02085 -0.0290 0.4247 1.0000
7.250 1.0529 0.02911 0.02092 -0.0282 0.4196 1.0000
7.500 1.0550 0.03024 0.02232 -0.0247 0.4118 1.0000
7.750 1.0801 0.03012 0.02217 -0.0239 0.4062 1.0000
8.000 1.0814 0.03125 0.02352 -0.0203 0.3988 1.0000
8.250 1.1007 0.03132 0.02362 -0.0187 0.3924 1.0000
8.500 1.1105 0.03193 0.02434 -0.0160 0.3859 1.0000
8.750 1.1191 0.03241 0.02495 -0.0131 0.3787 1.0000
9.000 1.1415 0.03233 0.02486 -0.0118 0.3724 1.0000
9.250 1.1364 0.03328 0.02601 -0.0071 0.3648 1.0000
9.500 1.1693 0.03266 0.02531 -0.0072 0.3580 1.0000
9.750 1.1558 0.03389 0.02680 -0.0014 0.3503 1.0000
10.000 1.1916 0.03309 0.02590 -0.0018 0.3427 1.0000
10.250 1.1826 0.03418 0.02722 0.0032 0.3344 1.0000
10.500 1.2095 0.03374 0.02677 0.0038 0.3260 1.0000
10.750 1.2225 0.03389 0.02703 0.0059 0.3167 1.0000
11.000 1.2303 0.03440 0.02767 0.0085 0.3074 1.0000
11.250 1.2599 0.03372 0.02693 0.0088 0.2973 1.0000
11.500 1.2677 0.03402 0.02735 0.0114 0.2870 1.0000
11.750 1.2715 0.03462 0.02809 0.0143 0.2769 1.0000
12.000 1.2855 0.03461 0.02810 0.0162 0.2660 1.0000
12.250 1.2999 0.03450 0.02794 0.0181 0.2545 1.0000
12.500 1.2921 0.03543 0.02901 0.0221 0.2448 1.0000
12.750 1.2874 0.03652 0.03018 0.0252 0.2349 1.0000
13.000 1.2897 0.03738 0.03102 0.0273 0.2240 1.0000
13.250 1.2931 0.03832 0.03190 0.0290 0.2126 1.0000
13.500 1.2803 0.04055 0.03427 0.0309 0.2034 1.0000
13.750 1.2725 0.04281 0.03659 0.0321 0.1936 1.0000
14.000 1.2706 0.04475 0.03849 0.0329 0.1833 1.0000
14.250 1.2717 0.04658 0.04022 0.0336 0.1723 1.0000
14.500 1.2527 0.05055 0.04442 0.0335 0.1653 1.0000
14.750 1.2494 0.05315 0.04698 0.0336 0.1560 1.0000
15.000 1.2528 0.05512 0.04880 0.0339 0.1458 1.0000
15.250 1.2317 0.05998 0.05393 0.0327 0.1404 1.0000
15.500 1.2344 0.06223 0.05607 0.0328 0.1315 1.0000
15.750 1.2173 0.06701 0.06107 0.0314 0.1262 1.0000
16.000 1.2201 0.06944 0.06342 0.0313 0.1183 1.0000
16.250 1.2029 0.07459 0.06877 0.0295 0.1138 1.0000
16.500 1.2090 0.07670 0.07078 0.0294 0.1062 1.0000
16.750 1.1875 0.08289 0.07723 0.0269 0.1030 1.0000
17.000 1.2026 0.08382 0.07797 0.0275 0.0949 1.0000
17.250 1.1779 0.09075 0.08519 0.0243 0.0932 1.0000
17.500 1.1530 0.09817 0.09285 0.0207 0.0915 1.0000
17.750 1.1239 0.10669 0.10160 0.0164 0.0905 1.0000
18.000 1.0662 0.12133 0.11649 0.0085 0.0932 1.0000
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Polar data table (+)
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