EPPLER 339 AIRFOIL (e339-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 339 AIRFOIL (e339-il) Reynolds number: 100,000 Max Cl/Cd: 34.2 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e339-il-100000.txt Download as CSV file: xf-e339-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 339 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2852 0.09860 0.09424 -0.0362 1.0000 0.0732
-8.500 -0.3026 0.09609 0.09186 -0.0399 1.0000 0.0740
-8.250 -0.3255 0.09386 0.08976 -0.0415 1.0000 0.0742
-8.000 -0.2910 0.08913 0.08507 -0.0366 1.0000 0.0778
-7.750 -0.2968 0.08658 0.08266 -0.0363 1.0000 0.0790
-7.500 -0.3692 0.08793 0.08430 -0.0326 0.9995 0.0755
-7.250 -0.3294 0.08321 0.07962 -0.0350 0.9921 0.0817
-7.000 -0.3202 0.07899 0.07488 -0.0517 0.9553 0.0865
-6.750 -0.2790 0.07144 0.06766 -0.0526 0.9489 0.0907
-6.500 -0.2517 0.06712 0.06316 -0.0591 0.9287 0.0979
-6.250 -0.2289 0.06195 0.05778 -0.0642 0.9095 0.1033
-6.000 -0.2067 0.06077 0.05604 -0.0677 0.8872 0.1155
-5.750 -0.1797 0.05429 0.04972 -0.0696 0.8687 0.1200
-5.500 -0.1685 0.05305 0.04795 -0.0696 0.8461 0.1335
-5.250 -0.1465 0.04889 0.04393 -0.0694 0.8262 0.1393
-5.000 -0.1355 0.04676 0.04152 -0.0682 0.8072 0.1538
-4.750 -0.1231 0.04478 0.03933 -0.0667 0.7900 0.1707
-4.500 -0.1092 0.04267 0.03710 -0.0651 0.7746 0.1895
-4.250 -0.0949 0.04058 0.03495 -0.0632 0.7599 0.2116
-4.000 -0.0847 0.03884 0.03314 -0.0609 0.7453 0.2448
-3.750 -0.0728 0.03727 0.03147 -0.0585 0.7321 0.2785
-3.500 -0.0562 0.03522 0.02938 -0.0563 0.7209 0.3062
-3.250 0.0136 0.03051 0.02203 -0.0561 0.7112 0.0731
-3.000 0.0406 0.02849 0.01942 -0.0543 0.7013 0.0634
-2.750 0.0663 0.02688 0.01759 -0.0534 0.6901 0.0623
-2.500 0.0925 0.02586 0.01623 -0.0522 0.6795 0.0635
-2.250 0.1212 0.02455 0.01466 -0.0515 0.6701 0.0646
-2.000 0.1489 0.02330 0.01339 -0.0510 0.6597 0.0663
-1.750 0.1776 0.02238 0.01239 -0.0505 0.6516 0.0707
-1.500 0.4143 0.01820 0.01060 -0.0833 0.6335 1.0000
-1.250 0.4350 0.01834 0.01056 -0.0823 0.6242 1.0000
-1.000 0.4569 0.01846 0.01043 -0.0813 0.6168 1.0000
-0.750 0.4781 0.01867 0.01049 -0.0804 0.6091 1.0000
-0.500 0.4997 0.01883 0.01048 -0.0795 0.6016 1.0000
-0.250 0.5220 0.01902 0.01047 -0.0786 0.5954 1.0000
0.000 0.5426 0.01927 0.01067 -0.0777 0.5875 1.0000
0.250 0.5652 0.01946 0.01069 -0.0768 0.5817 1.0000
0.500 0.5866 0.01977 0.01091 -0.0759 0.5757 1.0000
0.750 0.6076 0.02006 0.01116 -0.0749 0.5689 1.0000
1.000 0.6304 0.02027 0.01122 -0.0741 0.5636 1.0000
1.250 0.6511 0.02065 0.01156 -0.0731 0.5578 1.0000
1.500 0.6716 0.02103 0.01193 -0.0721 0.5518 1.0000
1.750 0.6942 0.02129 0.01209 -0.0713 0.5469 1.0000
2.000 0.7156 0.02168 0.01243 -0.0703 0.5421 1.0000
2.250 0.7340 0.02219 0.01300 -0.0691 0.5358 1.0000
2.500 0.7554 0.02255 0.01332 -0.0681 0.5310 1.0000
2.750 0.7789 0.02287 0.01353 -0.0674 0.5272 1.0000
3.000 0.7943 0.02360 0.01438 -0.0658 0.5212 1.0000
3.250 0.8135 0.02410 0.01490 -0.0645 0.5160 1.0000
3.500 0.8355 0.02445 0.01520 -0.0636 0.5119 1.0000
3.750 0.8556 0.02502 0.01575 -0.0625 0.5078 1.0000
4.000 0.8679 0.02592 0.01682 -0.0605 0.5018 1.0000
4.250 0.8875 0.02640 0.01730 -0.0593 0.4972 1.0000
4.500 0.9104 0.02674 0.01758 -0.0584 0.4936 1.0000
4.750 0.9220 0.02775 0.01872 -0.0563 0.4886 1.0000
5.000 0.9330 0.02872 0.01981 -0.0540 0.4830 1.0000
5.250 0.9540 0.02910 0.02020 -0.0529 0.4789 1.0000
5.500 0.9788 0.02938 0.02041 -0.0523 0.4755 1.0000
5.750 0.9756 0.03113 0.02241 -0.0484 0.4693 1.0000
6.000 0.9867 0.03202 0.02338 -0.0461 0.4642 1.0000
6.250 1.0121 0.03214 0.02348 -0.0455 0.4605 1.0000
6.500 1.0277 0.03290 0.02428 -0.0437 0.4565 1.0000
6.750 1.0085 0.03531 0.02695 -0.0379 0.4496 1.0000
7.000 1.0278 0.03564 0.02731 -0.0365 0.4453 1.0000
7.250 1.0630 0.03530 0.02691 -0.0370 0.4421 1.0000
7.500 1.0132 0.03915 0.03104 -0.0278 0.4347 1.0000
7.750 1.0136 0.04034 0.03229 -0.0243 0.4295 1.0000
8.000 1.0634 0.03915 0.03108 -0.0261 0.4264 1.0000
8.250 0.8414 0.05499 0.04703 -0.0075 0.4104 1.0000
8.500 0.9207 0.05005 0.04215 -0.0075 0.4103 1.0000
8.750 1.0347 0.04464 0.03681 -0.0134 0.4097 1.0000
9.000 0.8266 0.06470 0.05681 -0.0054 0.3905 1.0000
9.250 0.9026 0.05881 0.05102 -0.0035 0.3910 1.0000
9.500 0.9823 0.05323 0.04554 -0.0029 0.3908 1.0000
10.250 0.7418 0.08874 0.08098 -0.0071 0.3492 1.0000
10.500 0.7839 0.08692 0.07923 -0.0056 0.3451 1.0000
10.750 0.7495 0.09413 0.08646 -0.0073 0.3357 1.0000
11.000 0.7813 0.09336 0.08577 -0.0062 0.3302 1.0000
11.250 0.7658 0.09852 0.09097 -0.0073 0.3222 1.0000
11.500 0.7815 0.09972 0.09223 -0.0069 0.3158 1.0000
11.750 0.8336 0.09629 0.08891 -0.0047 0.3129 1.0000
12.000 0.7857 0.10576 0.09837 -0.0078 0.3016 1.0000
12.250 0.8352 0.10242 0.09515 -0.0055 0.2982 1.0000
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Polar data table (+)
Polar graphs
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