EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 431 AIRFOIL (e431-il) Reynolds number: 100,000 Max Cl/Cd: 46.24 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e431-il-100000-n5.txt Download as CSV file: xf-e431-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 431 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1790 0.09570 0.09074 -0.0905 0.9463 0.0219
-9.750 -0.1732 0.09082 0.08587 -0.0943 0.9397 0.0214
-9.250 -0.1697 0.07620 0.07126 -0.1077 0.9278 0.0190
-9.000 -0.1677 0.07008 0.06512 -0.1138 0.9197 0.0187
-8.750 -0.1696 0.06375 0.05869 -0.1204 0.9120 0.0184
-8.500 -0.1799 0.05863 0.05343 -0.1241 0.9018 0.0182
-8.250 -0.1928 0.05506 0.04970 -0.1243 0.8908 0.0179
-8.000 -0.1965 0.05079 0.04515 -0.1255 0.8840 0.0177
-7.750 -0.2043 0.04779 0.04191 -0.1236 0.8742 0.0175
-7.500 -0.2009 0.04396 0.03767 -0.1234 0.8685 0.0175
-7.250 -0.2006 0.04134 0.03471 -0.1211 0.8604 0.0176
-7.000 -0.1922 0.03809 0.03092 -0.1199 0.8547 0.0185
-6.750 -0.1741 0.03495 0.02717 -0.1197 0.8513 0.0189
-6.500 -0.1659 0.03362 0.02562 -0.1172 0.8436 0.0197
-6.250 -0.1444 0.03221 0.02400 -0.1170 0.8393 0.0210
-6.000 -0.1185 0.03005 0.02142 -0.1171 0.8363 0.0216
-5.750 -0.1007 0.02863 0.01970 -0.1155 0.8309 0.0221
-5.500 -0.0796 0.02723 0.01800 -0.1142 0.8260 0.0229
-5.250 -0.0533 0.02597 0.01662 -0.1141 0.8225 0.0241
-5.000 -0.0245 0.02488 0.01541 -0.1145 0.8198 0.0262
-4.750 -0.0087 0.02434 0.01481 -0.1125 0.8141 0.0292
-4.500 0.0122 0.02373 0.01411 -0.1115 0.8094 0.0327
-4.250 0.0376 0.02288 0.01323 -0.1113 0.8060 0.0375
-4.000 0.0661 0.02210 0.01239 -0.1116 0.8034 0.0476
-3.750 0.0790 0.02176 0.01213 -0.1092 0.7972 0.0601
-3.500 0.1001 0.02117 0.01166 -0.1083 0.7928 0.0918
-3.250 0.1249 0.02029 0.01119 -0.1083 0.7895 0.1693
-3.000 0.1483 0.01888 0.01071 -0.1086 0.7870 0.3808
-2.750 0.1462 0.01880 0.01174 -0.1021 0.7800 0.6074
-2.500 0.1654 0.01923 0.01216 -0.0994 0.7759 0.7025
-2.250 0.1913 0.01955 0.01229 -0.0982 0.7729 0.7461
-2.000 0.2162 0.01985 0.01245 -0.0964 0.7706 0.7719
-1.750 0.2200 0.02043 0.01299 -0.0917 0.7629 0.7888
-1.500 0.2379 0.02072 0.01318 -0.0889 0.7589 0.8118
-1.250 0.2550 0.02095 0.01334 -0.0850 0.7561 0.8346
-1.000 0.2619 0.02128 0.01363 -0.0803 0.7506 0.8532
-0.750 0.2749 0.02145 0.01372 -0.0774 0.7450 0.8642
-0.500 0.3031 0.02136 0.01348 -0.0775 0.7418 0.8702
-0.250 0.3361 0.02122 0.01318 -0.0787 0.7395 0.8749
0.000 0.3435 0.02153 0.01347 -0.0754 0.7324 0.8802
0.250 0.3670 0.02156 0.01340 -0.0749 0.7279 0.8849
0.500 0.3989 0.02146 0.01318 -0.0760 0.7250 0.8886
0.750 0.4343 0.02128 0.01289 -0.0775 0.7229 0.8913
1.000 0.4354 0.02177 0.01341 -0.0733 0.7141 0.8970
1.250 0.4645 0.02172 0.01328 -0.0739 0.7105 0.9008
1.500 0.4994 0.02157 0.01304 -0.0754 0.7080 0.9040
1.750 0.5088 0.02194 0.01343 -0.0726 0.7007 0.9089
2.000 0.5328 0.02201 0.01346 -0.0723 0.6957 0.9129
2.250 0.5670 0.02185 0.01325 -0.0736 0.6928 0.9164
2.750 0.6025 0.02227 0.01369 -0.0710 0.6805 0.9266
3.000 0.6376 0.02210 0.01349 -0.0724 0.6773 0.9298
3.250 0.6770 0.02183 0.01318 -0.0745 0.6749 0.9328
3.500 0.6751 0.02248 0.01393 -0.0701 0.6647 0.9420
3.750 0.7123 0.02226 0.01369 -0.0719 0.6614 0.9460
4.250 0.7568 0.02264 0.01417 -0.0710 0.6482 0.9597
4.500 0.7999 0.02228 0.01383 -0.0738 0.6449 0.9630
4.750 0.8159 0.02284 0.01447 -0.0729 0.6357 0.9772
5.000 0.8546 0.02255 0.01424 -0.0750 0.6308 0.9906
5.250 0.8725 0.02284 0.01457 -0.0740 0.6231 1.0000
5.500 0.8992 0.02287 0.01465 -0.0743 0.6162 1.0000
5.750 0.9296 0.02279 0.01462 -0.0750 0.6100 1.0000
6.000 0.9480 0.02314 0.01503 -0.0741 0.6010 1.0000
6.250 0.9748 0.02319 0.01513 -0.0744 0.5934 1.0000
6.500 0.9985 0.02334 0.01536 -0.0742 0.5847 1.0000
6.750 1.0171 0.02372 0.01581 -0.0733 0.5749 1.0000
7.000 1.0519 0.02341 0.01553 -0.0744 0.5671 1.0000
7.250 1.0642 0.02403 0.01625 -0.0728 0.5551 1.0000
7.500 1.0846 0.02433 0.01661 -0.0721 0.5439 1.0000
7.750 1.1118 0.02430 0.01662 -0.0722 0.5330 1.0000
8.000 1.1337 0.02452 0.01690 -0.0716 0.5205 1.0000
8.250 1.1493 0.02505 0.01749 -0.0704 0.5066 1.0000
8.500 1.1667 0.02551 0.01800 -0.0693 0.4922 1.0000
8.750 1.1841 0.02598 0.01852 -0.0683 0.4771 1.0000
9.000 1.2009 0.02650 0.01907 -0.0671 0.4612 1.0000
9.250 1.2168 0.02708 0.01966 -0.0659 0.4444 1.0000
9.500 1.2319 0.02773 0.02029 -0.0647 0.4270 1.0000
9.750 1.2433 0.02863 0.02122 -0.0631 0.4090 1.0000
10.000 1.2534 0.02964 0.02223 -0.0615 0.3905 1.0000
10.250 1.2628 0.03073 0.02332 -0.0599 0.3718 1.0000
10.500 1.2714 0.03191 0.02448 -0.0583 0.3534 1.0000
10.750 1.2788 0.03321 0.02576 -0.0567 0.3351 1.0000
11.000 1.2851 0.03463 0.02715 -0.0551 0.3173 1.0000
11.250 1.2904 0.03620 0.02873 -0.0536 0.2997 1.0000
11.500 1.2948 0.03787 0.03040 -0.0521 0.2823 1.0000
11.750 1.2987 0.03964 0.03217 -0.0507 0.2656 1.0000
12.000 1.3022 0.04150 0.03404 -0.0494 0.2494 1.0000
12.250 1.3050 0.04349 0.03605 -0.0481 0.2337 1.0000
12.500 1.3076 0.04556 0.03814 -0.0470 0.2189 1.0000
12.750 1.3095 0.04777 0.04037 -0.0460 0.2044 1.0000
13.000 1.3113 0.05008 0.04270 -0.0451 0.1907 1.0000
13.250 1.3124 0.05253 0.04517 -0.0443 0.1776 1.0000
13.500 1.3129 0.05511 0.04777 -0.0436 0.1653 1.0000
14.000 1.3132 0.06062 0.05338 -0.0427 0.1421 1.0000
14.250 1.3134 0.06350 0.05633 -0.0424 0.1315 1.0000
14.500 1.3125 0.06659 0.05946 -0.0422 0.1219 1.0000
14.750 1.3099 0.06995 0.06284 -0.0422 0.1132 1.0000
15.000 1.3097 0.07316 0.06616 -0.0423 0.1041 1.0000
15.250 1.3077 0.07663 0.06970 -0.0426 0.0966 1.0000
15.500 1.3045 0.08036 0.07349 -0.0430 0.0897 1.0000
15.750 1.3028 0.08396 0.07721 -0.0435 0.0831 1.0000
16.000 1.2984 0.08802 0.08132 -0.0443 0.0777 1.0000
16.250 1.2967 0.09179 0.08522 -0.0451 0.0720 1.0000
16.500 1.2922 0.09600 0.08950 -0.0461 0.0675 1.0000
16.750 1.2895 0.10002 0.09363 -0.0472 0.0631 1.0000
17.000 1.2859 0.10426 0.09799 -0.0485 0.0590 1.0000
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Polar data table (+)
Polar graphs
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