EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 395 AIRFOIL (e395-il) Reynolds number: 100,000 Max Cl/Cd: 59.77 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e395-il-100000.txt Download as CSV file: xf-e395-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3194 0.10103 0.09699 -0.0457 0.9756 0.1168
-7.250 -0.3245 0.09834 0.09433 -0.0504 0.9681 0.1232
-7.000 -0.3412 0.09466 0.09073 -0.0615 0.9571 0.1248
-6.750 -0.3737 0.06196 0.05770 -0.0888 0.9480 0.0580
-6.500 -0.3564 0.05303 0.04837 -0.0986 0.9428 0.0569
-6.250 -0.3296 0.04352 0.03782 -0.1090 0.9376 0.0575
-6.000 -0.2954 0.04070 0.03481 -0.1130 0.9337 0.0644
-5.750 -0.2492 0.03620 0.02947 -0.1197 0.9313 0.0740
-5.500 -0.2216 0.03422 0.02697 -0.1212 0.9257 0.0842
-5.250 -0.1866 0.03283 0.02525 -0.1235 0.9212 0.0973
-5.000 -0.1462 0.03152 0.02378 -0.1265 0.9178 0.1127
-4.750 -0.1168 0.03076 0.02286 -0.1275 0.9129 0.1270
-4.500 -0.0874 0.03008 0.02208 -0.1285 0.9074 0.1422
-4.250 -0.0489 0.02946 0.02142 -0.1308 0.9036 0.1618
-4.000 -0.0149 0.02906 0.02081 -0.1324 0.8993 0.1839
-3.750 0.0087 0.02884 0.02065 -0.1322 0.8929 0.2031
-3.500 0.0470 0.02855 0.02025 -0.1344 0.8889 0.2307
-3.250 0.0804 0.02839 0.02018 -0.1358 0.8847 0.2563
-3.000 0.1016 0.02846 0.02023 -0.1352 0.8777 0.2795
-2.750 0.1392 0.02830 0.02007 -0.1371 0.8737 0.3103
-2.500 0.1686 0.02837 0.02014 -0.1378 0.8687 0.3381
-2.250 0.1911 0.02851 0.02036 -0.1373 0.8619 0.3628
-2.000 0.2293 0.02839 0.02027 -0.1391 0.8582 0.3960
-1.750 0.2517 0.02866 0.02057 -0.1387 0.8519 0.4230
-1.500 0.2785 0.02879 0.02075 -0.1388 0.8459 0.4532
-1.250 0.3176 0.02863 0.02067 -0.1406 0.8425 0.4895
-1.000 0.3322 0.02915 0.02124 -0.1389 0.8346 0.5169
-0.750 0.3637 0.02916 0.02136 -0.1395 0.8296 0.5540
-0.500 0.4042 0.02892 0.02123 -0.1413 0.8268 0.5982
-0.250 0.4109 0.02968 0.02209 -0.1383 0.8173 0.6295
0.000 0.4452 0.02952 0.02206 -0.1389 0.8133 0.6798
0.250 0.4821 0.02918 0.02187 -0.1396 0.8106 0.7387
0.500 0.4795 0.03002 0.02287 -0.1349 0.7999 0.7884
1.000 0.5193 0.03032 0.02329 -0.1324 0.7864 1.0000
1.250 0.5638 0.03032 0.02310 -0.1355 0.7828 1.0000
1.500 0.6103 0.03016 0.02281 -0.1385 0.7801 1.0000
1.750 0.6161 0.03148 0.02406 -0.1362 0.7689 1.0000
2.000 0.6628 0.03117 0.02366 -0.1389 0.7664 1.0000
2.250 0.6677 0.03259 0.02505 -0.1364 0.7551 1.0000
2.500 0.7125 0.03226 0.02466 -0.1387 0.7521 1.0000
2.750 0.7607 0.03172 0.02409 -0.1414 0.7500 1.0000
3.000 0.7625 0.03329 0.02565 -0.1384 0.7377 1.0000
3.250 0.8120 0.03256 0.02493 -0.1410 0.7357 1.0000
3.500 0.8142 0.03417 0.02654 -0.1382 0.7233 1.0000
3.750 0.8638 0.03330 0.02570 -0.1406 0.7212 1.0000
4.000 0.8676 0.03485 0.02727 -0.1379 0.7089 1.0000
4.250 0.9183 0.03377 0.02623 -0.1403 0.7067 1.0000
4.500 0.9756 0.03245 0.02499 -0.1437 0.7052 1.0000
4.750 0.9760 0.03393 0.02650 -0.1401 0.6922 1.0000
5.000 0.9864 0.03500 0.02763 -0.1379 0.6810 1.0000
5.250 1.0397 0.03355 0.02629 -0.1404 0.6780 1.0000
5.500 1.1029 0.03167 0.02451 -0.1443 0.6760 1.0000
5.750 1.1115 0.03255 0.02547 -0.1415 0.6638 1.0000
6.000 1.1755 0.03044 0.02350 -0.1453 0.6610 1.0000
6.250 1.1915 0.03083 0.02399 -0.1432 0.6492 1.0000
6.500 1.2575 0.02851 0.02180 -0.1472 0.6450 1.0000
6.750 1.2759 0.02862 0.02203 -0.1453 0.6325 1.0000
7.000 1.3030 0.02824 0.02177 -0.1444 0.6206 1.0000
7.250 1.3400 0.02729 0.02095 -0.1447 0.6090 1.0000
7.500 1.3758 0.02634 0.02011 -0.1447 0.5957 1.0000
7.750 1.4034 0.02577 0.01963 -0.1437 0.5799 1.0000
8.000 1.4269 0.02536 0.01932 -0.1421 0.5622 1.0000
8.250 1.4514 0.02489 0.01893 -0.1405 0.5426 1.0000
8.500 1.4684 0.02478 0.01887 -0.1380 0.5207 1.0000
8.750 1.4822 0.02480 0.01892 -0.1350 0.4962 1.0000
9.000 1.4871 0.02517 0.01932 -0.1307 0.4700 1.0000
9.250 1.4906 0.02570 0.01981 -0.1264 0.4416 1.0000
9.500 1.4910 0.02650 0.02056 -0.1219 0.4108 1.0000
9.750 1.4884 0.02761 0.02155 -0.1173 0.3785 1.0000
10.000 1.4836 0.02906 0.02284 -0.1129 0.3453 1.0000
10.250 1.4765 0.03086 0.02448 -0.1086 0.3119 1.0000
10.500 1.4683 0.03298 0.02644 -0.1047 0.2791 1.0000
10.750 1.4596 0.03540 0.02867 -0.1011 0.2478 1.0000
11.000 1.4505 0.03807 0.03117 -0.0980 0.2184 1.0000
11.250 1.4415 0.04096 0.03389 -0.0952 0.1912 1.0000
11.500 1.4324 0.04408 0.03680 -0.0926 0.1672 1.0000
11.750 1.4250 0.04726 0.03988 -0.0905 0.1441 1.0000
12.000 1.4183 0.05056 0.04298 -0.0886 0.1253 1.0000
12.250 1.4142 0.05378 0.04618 -0.0869 0.1079 1.0000
12.500 1.4118 0.05696 0.04930 -0.0854 0.0938 1.0000
12.750 1.4116 0.06006 0.05237 -0.0841 0.0820 1.0000
13.000 1.4141 0.06302 0.05527 -0.0829 0.0721 1.0000
13.250 1.4213 0.06571 0.05780 -0.0817 0.0630 1.0000
13.500 1.4232 0.06878 0.06114 -0.0809 0.0568 1.0000
13.750 1.4367 0.07132 0.06365 -0.0797 0.0505 1.0000
14.000 1.4401 0.07439 0.06691 -0.0789 0.0462 1.0000
14.250 1.4553 0.07718 0.06969 -0.0780 0.0418 1.0000
14.500 1.4595 0.08078 0.07366 -0.0772 0.0395 1.0000
14.750 1.4609 0.08432 0.07741 -0.0768 0.0374 1.0000
15.000 1.4758 0.08775 0.08076 -0.0764 0.0344 1.0000
15.250 1.4623 0.09242 0.08582 -0.0765 0.0338 1.0000
15.500 1.4494 0.09753 0.09129 -0.0771 0.0331 1.0000
15.750 1.4364 0.10301 0.09711 -0.0780 0.0327 1.0000
16.000 1.4216 0.10892 0.10335 -0.0795 0.0325 1.0000
16.250 1.4052 0.11524 0.10997 -0.0817 0.0325 1.0000
16.500 1.3873 0.12204 0.11705 -0.0846 0.0325 1.0000
16.750 1.3683 0.12932 0.12460 -0.0883 0.0326 1.0000
17.000 1.3489 0.13705 0.13257 -0.0926 0.0329 1.0000
17.250 1.3287 0.14543 0.14116 -0.0978 0.0332 1.0000
17.500 1.3088 0.15430 0.15022 -0.1037 0.0335 1.0000
17.750 1.2902 0.16350 0.15956 -0.1100 0.0339 1.0000
18.000 1.2737 0.17283 0.16899 -0.1163 0.0343 1.0000
18.250 1.2048 0.20486 0.20112 -0.1380 0.0428 1.0000
18.500 1.1901 0.22399 0.22017 -0.1475 0.0529 1.0000
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Polar data table (+)
Polar graphs
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