EPPLER 407 AIRFOIL (e407-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 407 AIRFOIL (e407-il) Reynolds number: 500,000 Max Cl/Cd: 104.08 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e407-il-500000-n5.txt Download as CSV file: xf-e407-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 407 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4748 0.08242 0.07970 -0.1011 0.9831 0.0031
-13.500 -0.5047 0.07181 0.06893 -0.1067 0.9796 0.0030
-13.250 -0.5292 0.06220 0.05909 -0.1137 0.9770 0.0030
-13.000 -0.5457 0.05482 0.05149 -0.1196 0.9748 0.0029
-12.750 -0.5520 0.04962 0.04608 -0.1240 0.9731 0.0029
-12.500 -0.5580 0.04464 0.04086 -0.1281 0.9717 0.0029
-12.250 -0.5604 0.04017 0.03612 -0.1318 0.9705 0.0030
-12.000 -0.5681 0.03780 0.03361 -0.1305 0.9641 0.0029
-11.750 -0.5639 0.03494 0.03055 -0.1321 0.9615 0.0030
-11.500 -0.5539 0.03249 0.02791 -0.1339 0.9597 0.0030
-11.250 -0.5409 0.03013 0.02532 -0.1358 0.9583 0.0030
-11.000 -0.5327 0.02847 0.02351 -0.1356 0.9546 0.0030
-10.750 -0.5260 0.02701 0.02191 -0.1347 0.9500 0.0030
-10.500 -0.5101 0.02542 0.02018 -0.1355 0.9477 0.0031
-10.250 -0.4906 0.02394 0.01855 -0.1368 0.9460 0.0032
-10.000 -0.4696 0.02261 0.01710 -0.1380 0.9445 0.0032
-9.750 -0.4730 0.02175 0.01615 -0.1340 0.9375 0.0034
-9.500 -0.4583 0.02071 0.01500 -0.1336 0.9343 0.0034
-9.250 -0.4369 0.01966 0.01385 -0.1345 0.9324 0.0035
-9.000 -0.4132 0.01863 0.01271 -0.1357 0.9309 0.0036
-8.750 -0.4087 0.01806 0.01205 -0.1327 0.9248 0.0037
-8.500 -0.3866 0.01732 0.01123 -0.1330 0.9222 0.0038
-8.250 -0.3633 0.01634 0.01016 -0.1337 0.9202 0.0043
-8.000 -0.3364 0.01568 0.00943 -0.1348 0.9188 0.0047
-7.750 -0.3079 0.01507 0.00875 -0.1359 0.9177 0.0052
-7.500 -0.2922 0.01470 0.00832 -0.1343 0.9135 0.0059
-7.250 -0.2696 0.01421 0.00779 -0.1341 0.9106 0.0066
-7.000 -0.2428 0.01373 0.00726 -0.1347 0.9087 0.0082
-6.750 -0.2140 0.01324 0.00677 -0.1357 0.9071 0.0116
-6.500 -0.1837 0.01279 0.00632 -0.1370 0.9057 0.0178
-6.250 -0.1529 0.01230 0.00589 -0.1385 0.9045 0.0295
-6.000 -0.1225 0.01188 0.00550 -0.1398 0.9032 0.0426
-5.750 -0.1030 0.01157 0.00526 -0.1387 0.8993 0.0606
-5.500 -0.0756 0.01105 0.00490 -0.1395 0.8968 0.0985
-5.250 -0.0454 0.01055 0.00456 -0.1409 0.8950 0.1422
-5.000 -0.0134 0.01002 0.00421 -0.1427 0.8934 0.1940
-4.750 0.0197 0.00952 0.00386 -0.1446 0.8920 0.2495
-4.500 0.0548 0.00877 0.00345 -0.1474 0.8908 0.3473
-4.250 0.0909 0.00810 0.00320 -0.1502 0.8898 0.4738
-4.000 0.1159 0.00806 0.00322 -0.1498 0.8866 0.5041
-3.750 0.1437 0.00803 0.00320 -0.1500 0.8838 0.5237
-3.500 0.1735 0.00801 0.00317 -0.1505 0.8815 0.5388
-3.250 0.2045 0.00799 0.00311 -0.1513 0.8796 0.5502
-3.000 0.2363 0.00797 0.00304 -0.1523 0.8778 0.5596
-2.750 0.2686 0.00795 0.00300 -0.1533 0.8762 0.5669
-2.500 0.2945 0.00799 0.00300 -0.1531 0.8729 0.5744
-2.250 0.3213 0.00802 0.00305 -0.1529 0.8694 0.5812
-2.000 0.3513 0.00803 0.00301 -0.1535 0.8663 0.5897
-1.750 0.3826 0.00800 0.00298 -0.1542 0.8636 0.5944
-1.500 0.4122 0.00798 0.00294 -0.1547 0.8602 0.5974
-1.250 0.4378 0.00799 0.00294 -0.1543 0.8555 0.6004
-1.000 0.4674 0.00796 0.00287 -0.1548 0.8515 0.6032
-0.750 0.5000 0.00790 0.00279 -0.1559 0.8481 0.6054
-0.500 0.5233 0.00792 0.00284 -0.1550 0.8418 0.6076
-0.250 0.5524 0.00789 0.00281 -0.1553 0.8370 0.6100
0.000 0.5819 0.00788 0.00278 -0.1558 0.8323 0.6127
0.250 0.6077 0.00788 0.00280 -0.1554 0.8256 0.6152
0.500 0.6385 0.00786 0.00273 -0.1561 0.8198 0.6177
0.750 0.6634 0.00786 0.00277 -0.1556 0.8114 0.6198
1.000 0.6918 0.00786 0.00277 -0.1558 0.8041 0.6219
1.250 0.7186 0.00788 0.00280 -0.1556 0.7951 0.6240
1.500 0.7453 0.00790 0.00283 -0.1554 0.7852 0.6264
1.750 0.7723 0.00794 0.00284 -0.1553 0.7732 0.6290
2.000 0.7985 0.00799 0.00286 -0.1550 0.7581 0.6315
2.250 0.8239 0.00807 0.00290 -0.1545 0.7404 0.6335
2.500 0.8481 0.00818 0.00297 -0.1537 0.7206 0.6353
2.750 0.8701 0.00836 0.00307 -0.1525 0.6950 0.6375
3.000 0.8889 0.00862 0.00321 -0.1507 0.6624 0.6399
3.250 0.9040 0.00897 0.00339 -0.1481 0.6242 0.6424
3.500 0.9159 0.00935 0.00360 -0.1449 0.5858 0.6448
3.750 0.9274 0.00979 0.00386 -0.1416 0.5487 0.6470
4.000 0.9403 0.01024 0.00419 -0.1388 0.5108 0.6488
4.250 0.9535 0.01075 0.00454 -0.1360 0.4722 0.6510
4.500 0.9671 0.01131 0.00493 -0.1335 0.4320 0.6533
4.750 0.9827 0.01183 0.00530 -0.1314 0.3950 0.6558
5.000 0.9987 0.01237 0.00569 -0.1294 0.3601 0.6582
5.250 1.0156 0.01291 0.00609 -0.1276 0.3249 0.6605
5.500 1.0327 0.01346 0.00651 -0.1259 0.2916 0.6625
5.750 1.0497 0.01402 0.00695 -0.1242 0.2602 0.6646
6.000 1.0662 0.01464 0.00743 -0.1224 0.2252 0.6670
6.250 1.0832 0.01527 0.00792 -0.1208 0.1935 0.6696
6.500 1.1013 0.01584 0.00839 -0.1194 0.1694 0.6721
6.750 1.1185 0.01647 0.00892 -0.1179 0.1444 0.6746
7.000 1.1351 0.01715 0.00948 -0.1163 0.1185 0.6767
7.250 1.1529 0.01775 0.01003 -0.1149 0.0994 0.6788
7.500 1.1705 0.01837 0.01060 -0.1135 0.0837 0.6813
7.750 1.1875 0.01904 0.01122 -0.1120 0.0688 0.6840
8.000 1.2048 0.01970 0.01184 -0.1106 0.0568 0.6868
8.250 1.2227 0.02032 0.01245 -0.1093 0.0480 0.6894
8.500 1.2398 0.02098 0.01314 -0.1079 0.0402 0.6917
8.750 1.2562 0.02171 0.01387 -0.1064 0.0329 0.6940
9.000 1.2730 0.02241 0.01459 -0.1050 0.0277 0.6966
9.250 1.2891 0.02316 0.01538 -0.1036 0.0235 0.6995
9.500 1.3053 0.02392 0.01617 -0.1022 0.0202 0.7026
9.750 1.3202 0.02478 0.01706 -0.1006 0.0171 0.7054
10.000 1.3363 0.02553 0.01790 -0.0993 0.0154 0.7080
10.250 1.3512 0.02640 0.01884 -0.0978 0.0135 0.7107
10.500 1.3646 0.02740 0.01989 -0.0962 0.0118 0.7137
10.750 1.3795 0.02828 0.02085 -0.0948 0.0109 0.7168
11.000 1.3934 0.02923 0.02187 -0.0933 0.0097 0.7200
11.250 1.4057 0.03033 0.02303 -0.0917 0.0085 0.7230
11.500 1.4177 0.03148 0.02426 -0.0901 0.0077 0.7265
11.750 1.4303 0.03256 0.02545 -0.0887 0.0069 0.7300
12.000 1.4418 0.03377 0.02674 -0.0872 0.0063 0.7334
12.250 1.4520 0.03510 0.02816 -0.0856 0.0057 0.7366
12.500 1.4601 0.03667 0.02984 -0.0839 0.0051 0.7402
12.750 1.4697 0.03810 0.03140 -0.0825 0.0048 0.7442
13.250 1.4859 0.04135 0.03490 -0.0796 0.0041 0.7525
13.500 1.4927 0.04317 0.03682 -0.0782 0.0038 0.7570
13.750 1.4980 0.04518 0.03894 -0.0769 0.0035 0.7616
14.000 1.4997 0.04764 0.04154 -0.0755 0.0032 0.7658
14.250 1.5037 0.04991 0.04395 -0.0744 0.0031 0.7707
14.500 1.5069 0.05234 0.04653 -0.0734 0.0029 0.7760
14.750 1.5090 0.05497 0.04932 -0.0725 0.0028 0.7815
15.000 1.5104 0.05776 0.05226 -0.0718 0.0026 0.7880
15.250 1.5107 0.06080 0.05545 -0.0714 0.0025 0.7945
15.500 1.5104 0.06402 0.05884 -0.0711 0.0024 0.8019
15.750 1.5093 0.06748 0.06246 -0.0711 0.0023 0.8097
16.000 1.5070 0.07122 0.06635 -0.0713 0.0022 0.8184
16.250 1.5026 0.07540 0.07070 -0.0719 0.0021 0.8275
16.500 1.4962 0.08006 0.07554 -0.0728 0.0020 0.8379
16.750 1.4871 0.08532 0.08099 -0.0741 0.0019 0.8502
17.000 1.4763 0.09097 0.08684 -0.0758 0.0019 0.8665
17.250 1.4625 0.09700 0.09308 -0.0777 0.0019 0.8932
17.750 1.4292 0.11028 0.10675 -0.0827 0.0018 1.0000
18.000 1.4155 0.11756 0.11419 -0.0864 0.0018 1.0000
18.250 1.4004 0.12530 0.12210 -0.0907 0.0018 1.0000
18.500 1.3841 0.13348 0.13044 -0.0955 0.0018 1.0000
18.750 1.3701 0.14134 0.13845 -0.1002 0.0018 1.0000
19.000 1.3514 0.15045 0.14772 -0.1059 0.0018 1.0000
19.250 1.3359 0.15901 0.15642 -0.1114 0.0018 1.0000
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Polar data table (+)
Polar graphs
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