EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 68 AIRFOIL (e68-il) Reynolds number: 100,000 Max Cl/Cd: 56.54 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e68-il-100000-n5.txt Download as CSV file: xf-e68-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 68 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4439 0.09165 0.08678 -0.0539 1.0000 0.0277
-10.250 -0.4691 0.08463 0.07985 -0.0553 1.0000 0.0272
-10.000 -0.5247 0.07198 0.06726 -0.0607 1.0000 0.0262
-9.750 -0.5853 0.06323 0.05846 -0.0643 1.0000 0.0254
-9.500 -0.6214 0.05583 0.05072 -0.0708 0.9917 0.0249
-9.250 -0.6233 0.05000 0.04443 -0.0759 0.9835 0.0250
-9.000 -0.6192 0.04577 0.03979 -0.0777 0.9754 0.0252
-8.750 -0.6056 0.04212 0.03571 -0.0796 0.9700 0.0256
-8.500 -0.5921 0.03920 0.03239 -0.0801 0.9634 0.0261
-8.250 -0.5697 0.03643 0.02921 -0.0816 0.9593 0.0268
-8.000 -0.5517 0.03425 0.02669 -0.0814 0.9535 0.0276
-7.750 -0.5283 0.03220 0.02431 -0.0819 0.9487 0.0286
-7.500 -0.4994 0.03046 0.02220 -0.0831 0.9455 0.0302
-7.250 -0.4794 0.02918 0.02089 -0.0828 0.9397 0.0323
-7.000 -0.4533 0.02806 0.01964 -0.0834 0.9350 0.0349
-6.750 -0.4230 0.02674 0.01809 -0.0844 0.9318 0.0378
-6.500 -0.4008 0.02558 0.01685 -0.0841 0.9264 0.0408
-6.250 -0.3753 0.02461 0.01579 -0.0843 0.9213 0.0460
-6.000 -0.3445 0.02362 0.01475 -0.0856 0.9180 0.0558
-5.750 -0.3170 0.02282 0.01389 -0.0861 0.9136 0.0703
-5.500 -0.2931 0.02218 0.01327 -0.0859 0.9075 0.0880
-5.250 -0.2614 0.02157 0.01269 -0.0872 0.9041 0.1140
-5.000 -0.2268 0.02091 0.01207 -0.0890 0.9016 0.1412
-4.750 -0.2078 0.02051 0.01172 -0.0877 0.8939 0.1632
-4.500 -0.1762 0.02000 0.01124 -0.0888 0.8901 0.1935
-4.250 -0.1413 0.01949 0.01078 -0.0905 0.8875 0.2303
-4.000 -0.1202 0.01920 0.01058 -0.0895 0.8804 0.2638
-3.750 -0.0896 0.01881 0.01027 -0.0903 0.8762 0.3064
-3.500 -0.0550 0.01841 0.00997 -0.0918 0.8734 0.3533
-3.250 -0.0316 0.01822 0.00987 -0.0911 0.8668 0.3938
-3.000 -0.0026 0.01798 0.00970 -0.0913 0.8619 0.4367
-2.750 0.0319 0.01771 0.00950 -0.0925 0.8588 0.4808
-2.500 0.0556 0.01763 0.00947 -0.0917 0.8523 0.5176
-2.250 0.0838 0.01748 0.00937 -0.0916 0.8471 0.5538
-2.000 0.1176 0.01727 0.00919 -0.0925 0.8439 0.5904
-1.750 0.1392 0.01727 0.00924 -0.0911 0.8366 0.6212
-1.500 0.1682 0.01715 0.00915 -0.0910 0.8316 0.6531
-1.250 0.2017 0.01697 0.00898 -0.0917 0.8284 0.6846
-1.000 0.2200 0.01705 0.00910 -0.0896 0.8199 0.7109
-0.750 0.2505 0.01691 0.00898 -0.0897 0.8156 0.7393
-0.500 0.2751 0.01689 0.00897 -0.0887 0.8094 0.7663
-0.250 0.2992 0.01686 0.00895 -0.0876 0.8028 0.7926
0.000 0.3309 0.01668 0.00877 -0.0877 0.7991 0.8183
0.250 0.3477 0.01677 0.00889 -0.0852 0.7902 0.8444
0.500 0.3782 0.01660 0.00872 -0.0852 0.7856 0.8708
0.750 0.4011 0.01662 0.00875 -0.0839 0.7779 0.8983
1.000 0.4364 0.01649 0.00862 -0.0851 0.7724 0.9249
1.250 0.4803 0.01635 0.00846 -0.0881 0.7677 0.9494
1.500 0.5215 0.01636 0.00848 -0.0911 0.7597 0.9777
1.750 0.5667 0.01618 0.00825 -0.0946 0.7549 1.0000
2.000 0.5837 0.01633 0.00837 -0.0929 0.7450 1.0000
2.250 0.6177 0.01622 0.00821 -0.0940 0.7393 1.0000
2.500 0.6377 0.01638 0.00836 -0.0928 0.7292 1.0000
2.750 0.6659 0.01640 0.00836 -0.0929 0.7212 1.0000
3.000 0.6938 0.01643 0.00838 -0.0929 0.7126 1.0000
3.250 0.7181 0.01655 0.00850 -0.0923 0.7026 1.0000
3.500 0.7498 0.01651 0.00844 -0.0929 0.6944 1.0000
3.750 0.7737 0.01664 0.00859 -0.0922 0.6835 1.0000
4.000 0.7983 0.01676 0.00875 -0.0916 0.6726 1.0000
4.250 0.8257 0.01682 0.00882 -0.0915 0.6619 1.0000
4.500 0.8548 0.01685 0.00885 -0.0916 0.6511 1.0000
4.750 0.8779 0.01701 0.00906 -0.0907 0.6381 1.0000
5.000 0.9017 0.01716 0.00925 -0.0898 0.6247 1.0000
5.250 0.9256 0.01732 0.00943 -0.0891 0.6109 1.0000
5.500 0.9494 0.01748 0.00962 -0.0882 0.5963 1.0000
5.750 0.9728 0.01766 0.00984 -0.0873 0.5806 1.0000
6.000 0.9957 0.01785 0.01005 -0.0863 0.5640 1.0000
6.250 1.0171 0.01808 0.01030 -0.0850 0.5462 1.0000
6.500 1.0363 0.01837 0.01062 -0.0834 0.5269 1.0000
6.750 1.0556 0.01867 0.01094 -0.0819 0.5065 1.0000
7.000 1.0734 0.01902 0.01128 -0.0800 0.4846 1.0000
7.250 1.0895 0.01943 0.01166 -0.0780 0.4611 1.0000
7.500 1.1032 0.01987 0.01209 -0.0755 0.4366 1.0000
7.750 1.1157 0.02041 0.01256 -0.0729 0.4107 1.0000
8.000 1.1268 0.02103 0.01314 -0.0702 0.3839 1.0000
8.250 1.1366 0.02175 0.01378 -0.0674 0.3558 1.0000
8.500 1.1450 0.02258 0.01452 -0.0645 0.3268 1.0000
8.750 1.1526 0.02350 0.01535 -0.0617 0.2984 1.0000
9.000 1.1595 0.02453 0.01629 -0.0589 0.2707 1.0000
9.250 1.1662 0.02563 0.01732 -0.0563 0.2447 1.0000
9.500 1.1720 0.02684 0.01847 -0.0538 0.2201 1.0000
9.750 1.1775 0.02814 0.01970 -0.0513 0.1974 1.0000
10.000 1.1833 0.02950 0.02102 -0.0491 0.1756 1.0000
10.250 1.1877 0.03100 0.02246 -0.0468 0.1554 1.0000
10.500 1.1920 0.03259 0.02398 -0.0448 0.1355 1.0000
10.750 1.1955 0.03431 0.02563 -0.0428 0.1163 1.0000
11.000 1.1981 0.03616 0.02740 -0.0410 0.1000 1.0000
11.250 1.2018 0.03801 0.02923 -0.0394 0.0858 1.0000
11.500 1.2046 0.04000 0.03120 -0.0378 0.0743 1.0000
11.750 1.2080 0.04201 0.03330 -0.0364 0.0644 1.0000
12.000 1.2105 0.04417 0.03553 -0.0351 0.0565 1.0000
12.250 1.2096 0.04672 0.03809 -0.0339 0.0508 1.0000
12.500 1.2112 0.04913 0.04063 -0.0328 0.0453 1.0000
12.750 1.2078 0.05211 0.04360 -0.0319 0.0415 1.0000
13.000 1.2093 0.05470 0.04637 -0.0311 0.0376 1.0000
13.250 1.2085 0.05761 0.04938 -0.0306 0.0347 1.0000
13.750 1.2049 0.06397 0.05597 -0.0300 0.0310 1.0000
14.000 1.2047 0.06713 0.05929 -0.0298 0.0294 1.0000
14.250 1.2044 0.07037 0.06267 -0.0298 0.0282 1.0000
14.500 1.2036 0.07376 0.06620 -0.0300 0.0271 1.0000
14.750 1.2021 0.07729 0.06982 -0.0304 0.0262 1.0000
15.000 1.2007 0.08086 0.07346 -0.0308 0.0254 1.0000
15.250 1.2011 0.08439 0.07720 -0.0313 0.0245 1.0000
15.500 1.2003 0.08819 0.08122 -0.0320 0.0236 1.0000
15.750 1.1978 0.09231 0.08553 -0.0331 0.0227 1.0000
16.000 1.1944 0.09664 0.09004 -0.0345 0.0220 1.0000
16.250 1.1903 0.10117 0.09474 -0.0361 0.0214 1.0000
16.500 1.1857 0.10587 0.09960 -0.0379 0.0210 1.0000
16.750 1.1806 0.11076 0.10465 -0.0400 0.0206 1.0000
17.000 1.1747 0.11589 0.10994 -0.0423 0.0203 1.0000
17.250 1.1682 0.12129 0.11550 -0.0449 0.0201 1.0000
17.500 1.1607 0.12700 0.12136 -0.0479 0.0198 1.0000
17.750 1.1515 0.13324 0.12777 -0.0514 0.0197 1.0000
18.000 1.1401 0.14025 0.13496 -0.0556 0.0196 1.0000
18.250 1.1252 0.14845 0.14336 -0.0608 0.0196 1.0000
18.500 1.0997 0.16018 0.15536 -0.0686 0.0199 1.0000
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