EPPLER 407 AIRFOIL (e407-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 407 AIRFOIL (e407-il) Reynolds number: 1,000,000 Max Cl/Cd: 144.27 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e407-il-1000000.txt Download as CSV file: xf-e407-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4538 0.03828 0.03535 -0.1434 0.9717 0.0057
-11.000 -0.5087 0.02792 0.02410 -0.1433 0.9637 0.0042
-10.750 -0.4908 0.02593 0.02190 -0.1451 0.9619 0.0041
-10.500 -0.4695 0.02414 0.01994 -0.1471 0.9606 0.0040
-10.250 -0.4468 0.02260 0.01827 -0.1489 0.9593 0.0040
-10.000 -0.4230 0.02123 0.01677 -0.1505 0.9581 0.0039
-9.750 -0.4221 0.02015 0.01559 -0.1471 0.9519 0.0039
-9.500 -0.4063 0.01914 0.01449 -0.1465 0.9487 0.0039
-9.250 -0.3862 0.01810 0.01336 -0.1469 0.9466 0.0039
-9.000 -0.3648 0.01686 0.01199 -0.1476 0.9446 0.0039
-8.750 -0.3606 0.01593 0.01097 -0.1448 0.9389 0.0040
-8.500 -0.3416 0.01497 0.00992 -0.1448 0.9359 0.0040
-8.250 -0.3196 0.01391 0.00874 -0.1453 0.9336 0.0041
-8.000 -0.2942 0.01308 0.00783 -0.1461 0.9318 0.0043
-7.750 -0.2731 0.01257 0.00726 -0.1457 0.9291 0.0045
-7.500 -0.2522 0.01213 0.00678 -0.1450 0.9259 0.0050
-7.250 -0.2262 0.01169 0.00629 -0.1454 0.9236 0.0054
-7.000 -0.1984 0.01115 0.00568 -0.1461 0.9217 0.0069
-6.750 -0.1695 0.01060 0.00514 -0.1471 0.9201 0.0127
-6.500 -0.1397 0.01016 0.00475 -0.1482 0.9186 0.0236
-6.250 -0.1107 0.00985 0.00447 -0.1491 0.9168 0.0336
-6.000 -0.0865 0.00957 0.00424 -0.1489 0.9141 0.0471
-5.750 -0.0591 0.00920 0.00398 -0.1494 0.9117 0.0707
-5.500 -0.0297 0.00877 0.00368 -0.1505 0.9097 0.1076
-5.250 0.0015 0.00803 0.00329 -0.1524 0.9079 0.1953
-5.000 0.0344 0.00721 0.00289 -0.1547 0.9064 0.3067
-4.750 0.0685 0.00643 0.00253 -0.1572 0.9049 0.4365
-4.500 0.1000 0.00624 0.00244 -0.1584 0.9031 0.4862
-4.250 0.1276 0.00616 0.00242 -0.1586 0.9007 0.5131
-4.000 0.1566 0.00612 0.00239 -0.1590 0.8983 0.5346
-3.750 0.1865 0.00610 0.00235 -0.1595 0.8960 0.5475
-3.500 0.2171 0.00608 0.00231 -0.1603 0.8940 0.5563
-3.250 0.2481 0.00606 0.00226 -0.1610 0.8921 0.5646
-3.000 0.2796 0.00609 0.00224 -0.1619 0.8900 0.5716
-2.750 0.3066 0.00608 0.00223 -0.1618 0.8868 0.5771
-2.500 0.3350 0.00607 0.00222 -0.1620 0.8834 0.5822
-2.250 0.3652 0.00606 0.00217 -0.1626 0.8804 0.5875
-2.000 0.3958 0.00604 0.00212 -0.1633 0.8777 0.5920
-1.750 0.4252 0.00606 0.00214 -0.1637 0.8744 0.5968
-1.500 0.4526 0.00608 0.00215 -0.1636 0.8702 0.6026
-1.250 0.4817 0.00605 0.00212 -0.1640 0.8665 0.6069
-1.000 0.5120 0.00603 0.00209 -0.1646 0.8632 0.6095
-0.750 0.5401 0.00604 0.00209 -0.1647 0.8593 0.6120
-0.500 0.5677 0.00602 0.00207 -0.1647 0.8544 0.6145
-0.250 0.5973 0.00600 0.00202 -0.1652 0.8500 0.6169
0.000 0.6255 0.00599 0.00201 -0.1653 0.8453 0.6192
0.250 0.6526 0.00596 0.00201 -0.1652 0.8398 0.6214
0.500 0.6821 0.00596 0.00199 -0.1657 0.8349 0.6236
0.750 0.7084 0.00597 0.00202 -0.1654 0.8285 0.6260
1.000 0.7366 0.00597 0.00202 -0.1655 0.8217 0.6284
1.250 0.7630 0.00599 0.00204 -0.1653 0.8135 0.6306
1.500 0.7909 0.00602 0.00203 -0.1654 0.8056 0.6326
1.750 0.8170 0.00602 0.00207 -0.1651 0.7961 0.6350
2.000 0.8432 0.00606 0.00211 -0.1648 0.7856 0.6371
2.250 0.8685 0.00612 0.00216 -0.1643 0.7720 0.6392
2.500 0.8929 0.00622 0.00222 -0.1636 0.7557 0.6416
2.750 0.9161 0.00635 0.00229 -0.1626 0.7368 0.6440
3.000 0.9376 0.00653 0.00239 -0.1613 0.7119 0.6461
3.250 0.9557 0.00676 0.00251 -0.1593 0.6807 0.6482
3.500 0.9697 0.00711 0.00270 -0.1564 0.6396 0.6504
3.750 0.9812 0.00751 0.00293 -0.1531 0.5975 0.6526
4.000 0.9920 0.00791 0.00317 -0.1496 0.5579 0.6549
4.250 1.0042 0.00837 0.00346 -0.1466 0.5170 0.6573
4.500 1.0181 0.00886 0.00377 -0.1439 0.4764 0.6595
4.750 1.0327 0.00938 0.00409 -0.1415 0.4342 0.6614
5.000 1.0491 0.00984 0.00442 -0.1395 0.3955 0.6638
5.250 1.0640 0.01042 0.00480 -0.1372 0.3495 0.6660
5.500 1.0802 0.01097 0.00518 -0.1352 0.3107 0.6684
5.750 1.0972 0.01149 0.00555 -0.1334 0.2763 0.6709
6.000 1.1136 0.01209 0.00596 -0.1316 0.2377 0.6732
6.250 1.1304 0.01269 0.00638 -0.1298 0.2037 0.6753
6.500 1.1476 0.01325 0.00682 -0.1281 0.1740 0.6777
6.750 1.1648 0.01381 0.00728 -0.1265 0.1472 0.6800
7.000 1.1829 0.01434 0.00772 -0.1250 0.1249 0.6825
7.250 1.2006 0.01491 0.00820 -0.1235 0.1047 0.6851
7.500 1.2184 0.01548 0.00869 -0.1220 0.0869 0.6876
7.750 1.2354 0.01611 0.00922 -0.1204 0.0703 0.6899
8.000 1.2528 0.01670 0.00978 -0.1189 0.0564 0.6924
8.250 1.2702 0.01731 0.01035 -0.1174 0.0447 0.6949
8.500 1.2871 0.01795 0.01095 -0.1159 0.0353 0.6975
8.750 1.3045 0.01856 0.01155 -0.1144 0.0287 0.7003
9.000 1.3217 0.01920 0.01219 -0.1130 0.0233 0.7031
9.250 1.3380 0.01990 0.01287 -0.1114 0.0195 0.7057
9.500 1.3548 0.02055 0.01358 -0.1100 0.0167 0.7085
9.750 1.3724 0.02115 0.01422 -0.1087 0.0149 0.7113
10.000 1.3872 0.02198 0.01508 -0.1070 0.0126 0.7141
10.250 1.4032 0.02270 0.01586 -0.1055 0.0115 0.7171
10.500 1.4202 0.02334 0.01655 -0.1042 0.0105 0.7202
10.750 1.4351 0.02414 0.01738 -0.1027 0.0092 0.7234
11.000 1.4477 0.02516 0.01847 -0.1008 0.0078 0.7266
11.250 1.4638 0.02589 0.01925 -0.0995 0.0072 0.7300
11.500 1.4783 0.02673 0.02013 -0.0981 0.0064 0.7332
11.750 1.4874 0.02808 0.02154 -0.0960 0.0052 0.7365
12.000 1.5021 0.02892 0.02247 -0.0946 0.0048 0.7402
12.250 1.5152 0.02993 0.02356 -0.0931 0.0043 0.7442
12.500 1.5263 0.03110 0.02478 -0.0915 0.0038 0.7481
12.750 1.5323 0.03278 0.02657 -0.0893 0.0033 0.7520
13.000 1.5406 0.03426 0.02816 -0.0875 0.0031 0.7564
13.250 1.5502 0.03563 0.02962 -0.0860 0.0029 0.7609
13.500 1.5585 0.03715 0.03125 -0.0844 0.0027 0.7653
13.750 1.5660 0.03878 0.03298 -0.0828 0.0026 0.7704
14.000 1.5726 0.04053 0.03484 -0.0813 0.0024 0.7760
14.250 1.5787 0.04239 0.03681 -0.0799 0.0023 0.7819
14.500 1.5831 0.04445 0.03898 -0.0785 0.0022 0.7886
14.750 1.5852 0.04684 0.04151 -0.0771 0.0021 0.7955
15.000 1.5851 0.04954 0.04435 -0.0758 0.0020 0.8034
15.250 1.5815 0.05277 0.04774 -0.0746 0.0020 0.8116
15.500 1.5748 0.05650 0.05165 -0.0736 0.0019 0.8210
15.750 1.5633 0.06103 0.05640 -0.0729 0.0018 0.8314
16.000 1.5516 0.06586 0.06144 -0.0727 0.0018 0.8440
16.250 1.5478 0.06975 0.06551 -0.0728 0.0018 0.8643
16.500 1.5406 0.07377 0.06977 -0.0727 0.0018 0.9149
16.750 1.5305 0.07814 0.07432 -0.0728 0.0018 1.0000
17.000 1.5228 0.08324 0.07956 -0.0741 0.0018 1.0000
17.250 1.5129 0.08891 0.08537 -0.0760 0.0017 1.0000
17.500 1.5019 0.09499 0.09160 -0.0782 0.0017 1.0000
17.750 1.4895 0.10154 0.09829 -0.0810 0.0017 1.0000
18.000 1.4751 0.10870 0.10560 -0.0843 0.0017 1.0000
18.250 1.4592 0.11637 0.11343 -0.0882 0.0017 1.0000
18.500 1.4424 0.12440 0.12162 -0.0926 0.0017 1.0000
18.750 1.4284 0.13203 0.12938 -0.0969 0.0017 1.0000
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Polar data table (+)
Polar graphs
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