EPPLER 1210 AIRFOIL (e1210-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 1210 AIRFOIL (e1210-il) Reynolds number: 100,000 Max Cl/Cd: 35.26 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1210-il-100000.txt Download as CSV file: xf-e1210-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1210 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1720 0.11007 0.10560 -0.0318 1.0000 0.1234
-9.250 -0.1784 0.10834 0.10400 -0.0326 1.0000 0.1281
-9.000 -0.2154 0.10879 0.10471 -0.0338 1.0000 0.1297
-8.750 -0.1903 0.10413 0.10014 -0.0334 0.9939 0.1321
-8.500 -0.1507 0.09931 0.09530 -0.0386 0.9748 0.1383
-8.250 -0.1488 0.09451 0.09050 -0.0514 0.9475 0.1447
-8.000 -0.0928 0.08953 0.08544 -0.0530 0.9332 0.1519
-7.750 -0.0874 0.08443 0.08027 -0.0671 0.9084 0.1599
-7.500 -0.0297 0.08012 0.07580 -0.0681 0.8882 0.1685
-7.250 -0.0666 0.07747 0.07306 -0.0802 0.8549 0.1757
-7.000 -0.0014 0.07367 0.06908 -0.0744 0.8363 0.1817
-6.750 -0.0151 0.07222 0.06756 -0.0771 0.8139 0.1909
-6.500 -0.0168 0.06875 0.06403 -0.0793 0.7968 0.1952
-6.250 0.0116 0.06691 0.06206 -0.0757 0.7800 0.2014
-6.000 -0.0488 0.05166 0.04617 -0.0985 0.7721 0.1587
-5.750 -0.0314 0.04892 0.04343 -0.0973 0.7589 0.1603
-5.500 -0.0173 0.04522 0.03952 -0.0980 0.7457 0.1555
-5.250 -0.0052 0.04096 0.03490 -0.0995 0.7340 0.1538
-5.000 0.0102 0.03704 0.03044 -0.1007 0.7230 0.1552
-4.750 0.0279 0.03399 0.02674 -0.1012 0.7112 0.1579
-4.500 0.0509 0.03247 0.02510 -0.1006 0.7005 0.1620
-4.250 0.0735 0.03158 0.02415 -0.0999 0.6877 0.1663
-4.000 0.0986 0.03013 0.02222 -0.0997 0.6784 0.1715
-3.750 0.1216 0.02878 0.02046 -0.0993 0.6661 0.1761
-3.250 0.1718 0.02730 0.01881 -0.0981 0.6450 0.1868
-3.000 0.1999 0.02659 0.01757 -0.0977 0.6367 0.1930
-2.750 0.2234 0.02583 0.01690 -0.0971 0.6251 0.1985
-2.500 0.2512 0.02535 0.01621 -0.0966 0.6169 0.2057
-2.250 0.2765 0.02496 0.01561 -0.0960 0.6060 0.2123
-2.000 0.3036 0.02439 0.01501 -0.0956 0.5977 0.2197
-1.750 0.3293 0.02419 0.01469 -0.0950 0.5881 0.2278
-1.500 0.3562 0.02373 0.01417 -0.0945 0.5795 0.2362
-1.250 0.3829 0.02356 0.01391 -0.0940 0.5713 0.2461
-1.000 0.4087 0.02328 0.01363 -0.0934 0.5620 0.2563
-0.750 0.4376 0.02308 0.01327 -0.0930 0.5554 0.2695
-0.500 0.4611 0.02299 0.01336 -0.0922 0.5460 0.2824
-0.250 0.4883 0.02276 0.01310 -0.0917 0.5386 0.2998
0.000 0.5141 0.02268 0.01309 -0.0911 0.5313 0.3217
0.250 0.5386 0.02257 0.01316 -0.0903 0.5229 0.3519
0.500 0.5658 0.02223 0.01299 -0.0898 0.5170 0.4056
0.750 0.5864 0.02187 0.01334 -0.0883 0.5096 0.5426
1.000 0.6250 0.02091 0.01333 -0.0884 0.5015 1.0000
1.250 0.6545 0.02118 0.01321 -0.0884 0.4960 1.0000
1.500 0.6755 0.02177 0.01378 -0.0874 0.4880 1.0000
1.750 0.7015 0.02211 0.01394 -0.0869 0.4816 1.0000
2.000 0.7309 0.02241 0.01394 -0.0868 0.4766 1.0000
2.250 0.7509 0.02308 0.01467 -0.0857 0.4690 1.0000
2.500 0.7764 0.02347 0.01493 -0.0851 0.4628 1.0000
2.750 0.8055 0.02377 0.01500 -0.0850 0.4582 1.0000
3.000 0.8256 0.02455 0.01583 -0.0840 0.4516 1.0000
3.250 0.8491 0.02508 0.01631 -0.0833 0.4454 1.0000
3.500 0.8774 0.02536 0.01642 -0.0831 0.4406 1.0000
3.750 0.9008 0.02607 0.01707 -0.0824 0.4354 1.0000
4.000 0.9199 0.02692 0.01801 -0.0813 0.4293 1.0000
4.250 0.9455 0.02737 0.01837 -0.0809 0.4243 1.0000
4.500 0.9756 0.02767 0.01846 -0.0809 0.4203 1.0000
4.750 0.9905 0.02883 0.01978 -0.0794 0.4144 1.0000
5.000 1.0106 0.02964 0.02062 -0.0785 0.4089 1.0000
5.250 1.0369 0.03010 0.02099 -0.0782 0.4048 1.0000
5.500 1.0677 0.03047 0.02118 -0.0783 0.4014 1.0000
5.750 1.0746 0.03214 0.02311 -0.0762 0.3955 1.0000
6.000 1.0923 0.03311 0.02413 -0.0750 0.3905 1.0000
6.250 1.1191 0.03351 0.02445 -0.0747 0.3865 1.0000
6.500 1.1511 0.03381 0.02459 -0.0750 0.3834 1.0000
6.750 1.1493 0.03616 0.02724 -0.0723 0.3783 1.0000
7.000 1.1542 0.03803 0.02926 -0.0702 0.3733 1.0000
7.250 1.1788 0.03856 0.02974 -0.0697 0.3696 1.0000
7.500 1.2129 0.03858 0.02963 -0.0701 0.3665 1.0000
7.750 1.2163 0.04070 0.03189 -0.0680 0.3625 1.0000
8.000 0.9069 0.07234 0.06445 -0.0602 0.3463 1.0000
8.250 0.9710 0.06687 0.05888 -0.0574 0.3462 1.0000
8.500 1.0402 0.06150 0.05342 -0.0552 0.3461 1.0000
8.750 1.1347 0.05514 0.04691 -0.0549 0.3459 1.0000
10.250 0.6946 0.13810 0.13076 -0.0824 0.3546 1.0000
10.500 0.7144 0.14042 0.13306 -0.0824 0.3508 1.0000
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Polar data table (+)
Polar graphs
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