EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 395 AIRFOIL (e395-il) Reynolds number: 100,000 Max Cl/Cd: 61.37 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e395-il-100000-n5.txt Download as CSV file: xf-e395-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 395 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2791 0.09330 0.08863 -0.0688 0.9752 0.0244
-9.250 -0.2810 0.08597 0.08133 -0.0746 0.9685 0.0248
-8.750 -0.3650 0.05468 0.04993 -0.1004 0.9382 0.0209
-8.500 -0.3672 0.04330 0.03793 -0.1183 0.9248 0.0204
-8.250 -0.3452 0.03982 0.03422 -0.1240 0.9188 0.0218
-8.000 -0.3241 0.03640 0.03038 -0.1283 0.9123 0.0236
-7.750 -0.3007 0.03251 0.02585 -0.1320 0.9061 0.0259
-7.500 -0.2679 0.03058 0.02375 -0.1353 0.9030 0.0287
-7.250 -0.2412 0.02869 0.02153 -0.1371 0.8975 0.0332
-7.000 -0.2124 0.02714 0.01971 -0.1387 0.8922 0.0383
-6.750 -0.1780 0.02578 0.01818 -0.1412 0.8890 0.0454
-6.500 -0.1416 0.02451 0.01672 -0.1439 0.8865 0.0541
-6.250 -0.1189 0.02369 0.01575 -0.1437 0.8791 0.0619
-6.000 -0.0857 0.02277 0.01465 -0.1454 0.8752 0.0723
-5.750 -0.0497 0.02192 0.01363 -0.1474 0.8724 0.0844
-5.500 -0.0231 0.02139 0.01297 -0.1477 0.8664 0.0957
-5.250 0.0075 0.02080 0.01231 -0.1487 0.8617 0.1088
-5.000 0.0423 0.02021 0.01159 -0.1503 0.8584 0.1248
-4.750 0.0743 0.01974 0.01109 -0.1515 0.8543 0.1416
-4.500 0.1004 0.01945 0.01077 -0.1515 0.8481 0.1580
-4.250 0.1337 0.01908 0.01034 -0.1528 0.8443 0.1781
-4.000 0.1693 0.01870 0.00987 -0.1544 0.8414 0.2006
-3.750 0.1924 0.01861 0.00978 -0.1538 0.8344 0.2188
-3.500 0.2238 0.01839 0.00952 -0.1546 0.8300 0.2410
-3.250 0.2583 0.01812 0.00919 -0.1559 0.8268 0.2645
-3.000 0.2828 0.01809 0.00916 -0.1555 0.8205 0.2846
-2.750 0.3125 0.01797 0.00899 -0.1559 0.8157 0.3080
-2.500 0.3457 0.01776 0.00877 -0.1569 0.8122 0.3313
-2.250 0.3714 0.01776 0.00876 -0.1567 0.8065 0.3537
-2.000 0.3989 0.01771 0.00873 -0.1567 0.8012 0.3768
-1.750 0.4311 0.01757 0.00856 -0.1575 0.7974 0.4030
-1.500 0.4574 0.01757 0.00861 -0.1572 0.7921 0.4270
-1.250 0.4838 0.01759 0.00866 -0.1570 0.7864 0.4527
-1.000 0.5151 0.01748 0.00856 -0.1576 0.7825 0.4817
-0.750 0.5416 0.01750 0.00864 -0.1573 0.7774 0.5097
-0.500 0.5666 0.01756 0.00877 -0.1568 0.7715 0.5392
-0.250 0.5970 0.01748 0.00872 -0.1571 0.7674 0.5725
0.000 0.6228 0.01753 0.00884 -0.1567 0.7622 0.6063
0.250 0.6466 0.01760 0.00901 -0.1558 0.7561 0.6414
0.500 0.6752 0.01752 0.00900 -0.1557 0.7521 0.6808
0.750 0.6972 0.01759 0.00918 -0.1544 0.7462 0.7215
1.000 0.7182 0.01762 0.00933 -0.1528 0.7403 0.7670
1.250 0.7420 0.01745 0.00926 -0.1514 0.7362 0.8224
1.500 0.7558 0.01747 0.00942 -0.1483 0.7294 0.9078
1.750 0.7867 0.01750 0.00940 -0.1490 0.7239 1.0000
2.000 0.8213 0.01752 0.00933 -0.1503 0.7201 1.0000
2.250 0.8424 0.01791 0.00974 -0.1494 0.7123 1.0000
2.500 0.8734 0.01800 0.00978 -0.1501 0.7073 1.0000
2.750 0.9004 0.01822 0.00999 -0.1500 0.7014 1.0000
3.000 0.9260 0.01846 0.01024 -0.1498 0.6946 1.0000
3.250 0.9590 0.01847 0.01022 -0.1506 0.6901 1.0000
3.500 0.9792 0.01887 0.01067 -0.1495 0.6818 1.0000
3.750 1.0100 0.01892 0.01073 -0.1499 0.6762 1.0000
4.000 1.0323 0.01923 0.01110 -0.1491 0.6682 1.0000
4.250 1.0613 0.01931 0.01120 -0.1492 0.6617 1.0000
4.500 1.0841 0.01959 0.01154 -0.1484 0.6534 1.0000
4.750 1.1130 0.01965 0.01164 -0.1484 0.6461 1.0000
5.000 1.1341 0.01994 0.01202 -0.1473 0.6367 1.0000
5.250 1.1651 0.01990 0.01200 -0.1476 0.6292 1.0000
5.500 1.1839 0.02023 0.01245 -0.1460 0.6183 1.0000
5.750 1.2065 0.02043 0.01273 -0.1450 0.6080 1.0000
6.000 1.2332 0.02048 0.01283 -0.1446 0.5981 1.0000
6.250 1.2544 0.02070 0.01316 -0.1433 0.5861 1.0000
6.500 1.2741 0.02097 0.01352 -0.1418 0.5733 1.0000
6.750 1.2943 0.02121 0.01385 -0.1404 0.5599 1.0000
7.000 1.3141 0.02146 0.01417 -0.1389 0.5453 1.0000
7.250 1.3330 0.02172 0.01452 -0.1372 0.5295 1.0000
7.500 1.3506 0.02202 0.01486 -0.1353 0.5122 1.0000
7.750 1.3656 0.02238 0.01524 -0.1329 0.4934 1.0000
8.000 1.3766 0.02290 0.01581 -0.1301 0.4726 1.0000
8.250 1.3886 0.02345 0.01633 -0.1274 0.4499 1.0000
8.500 1.3971 0.02417 0.01708 -0.1243 0.4249 1.0000
8.750 1.4043 0.02503 0.01788 -0.1212 0.3980 1.0000
9.000 1.4094 0.02606 0.01885 -0.1180 0.3697 1.0000
9.250 1.4123 0.02731 0.02000 -0.1147 0.3404 1.0000
9.500 1.4134 0.02877 0.02135 -0.1115 0.3110 1.0000
9.750 1.4133 0.03043 0.02290 -0.1084 0.2823 1.0000
10.000 1.4122 0.03229 0.02465 -0.1054 0.2549 1.0000
10.250 1.4113 0.03428 0.02657 -0.1028 0.2281 1.0000
10.500 1.4104 0.03640 0.02862 -0.1004 0.2031 1.0000
10.750 1.4090 0.03869 0.03082 -0.0982 0.1800 1.0000
11.000 1.4081 0.04104 0.03312 -0.0963 0.1580 1.0000
11.250 1.4069 0.04355 0.03556 -0.0945 0.1386 1.0000
11.500 1.4066 0.04607 0.03806 -0.0929 0.1203 1.0000
11.750 1.4057 0.04874 0.04071 -0.0915 0.1045 1.0000
12.000 1.4046 0.05154 0.04350 -0.0903 0.0908 1.0000
12.250 1.4036 0.05443 0.04643 -0.0891 0.0790 1.0000
12.500 1.4022 0.05746 0.04949 -0.0882 0.0690 1.0000
12.750 1.3999 0.06071 0.05277 -0.0874 0.0609 1.0000
13.000 1.3976 0.06406 0.05617 -0.0868 0.0538 1.0000
13.250 1.3962 0.06741 0.05961 -0.0863 0.0477 1.0000
13.500 1.3918 0.07123 0.06348 -0.0860 0.0433 1.0000
13.750 1.3908 0.07473 0.06713 -0.0858 0.0387 1.0000
14.000 1.3871 0.07868 0.07116 -0.0859 0.0355 1.0000
14.250 1.3840 0.08265 0.07525 -0.0861 0.0326 1.0000
14.500 1.3820 0.08656 0.07931 -0.0864 0.0298 1.0000
14.750 1.3772 0.09094 0.08377 -0.0871 0.0279 1.0000
15.000 1.3749 0.09502 0.08800 -0.0876 0.0260 1.0000
15.250 1.3731 0.09912 0.09229 -0.0884 0.0241 1.0000
15.500 1.3698 0.10351 0.09679 -0.0895 0.0226 1.0000
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Polar data table (+)
Polar graphs
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