EPPLER 407 AIRFOIL (e407-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 407 AIRFOIL (e407-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.51 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e407-il-1000000-n5.txt Download as CSV file: xf-e407-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.5226 0.09018 0.08800 -0.1012 0.9852 0.0019
-15.000 -0.5540 0.07810 0.07576 -0.1084 0.9846 0.0019
-14.750 -0.5693 0.06948 0.06700 -0.1147 0.9841 0.0018
-14.500 -0.5891 0.06047 0.05779 -0.1218 0.9835 0.0018
-14.250 -0.5899 0.05561 0.05283 -0.1260 0.9827 0.0018
-14.000 -0.6059 0.05046 0.04753 -0.1281 0.9789 0.0018
-13.750 -0.6190 0.04489 0.04175 -0.1318 0.9766 0.0018
-13.500 -0.6188 0.04125 0.03797 -0.1346 0.9750 0.0018
-13.250 -0.6206 0.03732 0.03384 -0.1376 0.9734 0.0018
-13.000 -0.6147 0.03425 0.03061 -0.1403 0.9721 0.0018
-12.750 -0.6021 0.03193 0.02815 -0.1429 0.9711 0.0018
-12.500 -0.5983 0.02971 0.02579 -0.1434 0.9676 0.0018
-12.250 -0.5926 0.02750 0.02342 -0.1441 0.9635 0.0018
-12.000 -0.5764 0.02578 0.02157 -0.1458 0.9612 0.0018
-11.750 -0.5585 0.02408 0.01975 -0.1477 0.9591 0.0019
-11.500 -0.5371 0.02266 0.01821 -0.1498 0.9574 0.0019
-11.250 -0.5314 0.02151 0.01696 -0.1482 0.9510 0.0019
-11.000 -0.5140 0.02036 0.01571 -0.1488 0.9473 0.0019
-10.750 -0.4936 0.01924 0.01448 -0.1499 0.9446 0.0019
-10.500 -0.4847 0.01834 0.01350 -0.1483 0.9388 0.0019
-10.250 -0.4705 0.01740 0.01247 -0.1477 0.9342 0.0019
-10.000 -0.4529 0.01655 0.01153 -0.1477 0.9308 0.0020
-9.750 -0.4480 0.01583 0.01074 -0.1451 0.9248 0.0020
-9.500 -0.4297 0.01514 0.00997 -0.1449 0.9210 0.0020
-9.250 -0.4081 0.01445 0.00920 -0.1453 0.9182 0.0020
-9.000 -0.3886 0.01386 0.00853 -0.1450 0.9151 0.0021
-8.750 -0.3687 0.01337 0.00799 -0.1445 0.9118 0.0021
-8.500 -0.3461 0.01291 0.00747 -0.1444 0.9089 0.0022
-8.250 -0.3227 0.01233 0.00681 -0.1446 0.9064 0.0024
-8.000 -0.2968 0.01188 0.00630 -0.1451 0.9043 0.0026
-7.750 -0.2722 0.01151 0.00590 -0.1452 0.9020 0.0029
-7.500 -0.2479 0.01118 0.00555 -0.1451 0.8994 0.0034
-7.250 -0.2222 0.01089 0.00521 -0.1453 0.8971 0.0037
-7.000 -0.1957 0.01055 0.00486 -0.1456 0.8948 0.0047
-6.750 -0.1680 0.01026 0.00454 -0.1462 0.8927 0.0062
-6.500 -0.1395 0.00997 0.00424 -0.1469 0.8909 0.0085
-6.250 -0.1115 0.00968 0.00397 -0.1475 0.8890 0.0137
-6.000 -0.0849 0.00943 0.00373 -0.1477 0.8867 0.0193
-5.750 -0.0576 0.00919 0.00351 -0.1481 0.8843 0.0252
-5.500 -0.0296 0.00893 0.00329 -0.1487 0.8821 0.0358
-5.250 -0.0008 0.00847 0.00300 -0.1497 0.8799 0.0744
-5.000 0.0292 0.00800 0.00272 -0.1509 0.8779 0.1232
-4.750 0.0599 0.00761 0.00248 -0.1522 0.8761 0.1717
-4.500 0.0889 0.00731 0.00230 -0.1530 0.8739 0.2092
-4.250 0.1182 0.00697 0.00212 -0.1539 0.8715 0.2586
-4.000 0.1495 0.00634 0.00183 -0.1557 0.8691 0.3603
-3.750 0.1813 0.00587 0.00165 -0.1572 0.8668 0.4515
-3.500 0.2119 0.00575 0.00158 -0.1581 0.8645 0.4846
-3.250 0.2426 0.00568 0.00153 -0.1589 0.8623 0.5079
-3.000 0.2714 0.00564 0.00151 -0.1593 0.8596 0.5220
-2.750 0.2999 0.00562 0.00149 -0.1596 0.8559 0.5325
-2.500 0.3290 0.00560 0.00146 -0.1600 0.8520 0.5412
-2.250 0.3589 0.00559 0.00142 -0.1605 0.8484 0.5487
-2.000 0.3870 0.00558 0.00142 -0.1607 0.8443 0.5558
-1.750 0.4155 0.00558 0.00141 -0.1609 0.8393 0.5629
-1.500 0.4447 0.00559 0.00140 -0.1613 0.8344 0.5713
-1.250 0.4726 0.00560 0.00141 -0.1614 0.8289 0.5764
-1.000 0.5010 0.00561 0.00140 -0.1617 0.8234 0.5792
-0.750 0.5294 0.00562 0.00140 -0.1619 0.8179 0.5818
-0.500 0.5571 0.00564 0.00140 -0.1619 0.8105 0.5845
-0.250 0.5849 0.00567 0.00140 -0.1620 0.8028 0.5870
0.000 0.6122 0.00571 0.00141 -0.1620 0.7938 0.5892
0.250 0.6395 0.00574 0.00143 -0.1620 0.7845 0.5914
0.500 0.6663 0.00579 0.00146 -0.1618 0.7741 0.5937
0.750 0.6924 0.00586 0.00150 -0.1616 0.7619 0.5961
1.000 0.7175 0.00596 0.00155 -0.1611 0.7457 0.5984
1.250 0.7409 0.00610 0.00161 -0.1602 0.7244 0.6008
1.500 0.7631 0.00628 0.00169 -0.1590 0.7000 0.6030
1.750 0.7839 0.00649 0.00180 -0.1576 0.6730 0.6050
2.000 0.8028 0.00676 0.00195 -0.1558 0.6413 0.6070
2.250 0.8196 0.00709 0.00213 -0.1536 0.6047 0.6093
2.500 0.8349 0.00747 0.00233 -0.1511 0.5644 0.6117
2.750 0.8504 0.00782 0.00253 -0.1487 0.5278 0.6140
3.000 0.8666 0.00818 0.00274 -0.1465 0.4926 0.6160
3.500 0.9027 0.00893 0.00322 -0.1429 0.4237 0.6201
3.750 0.9204 0.00937 0.00350 -0.1411 0.3865 0.6223
4.000 0.9389 0.00978 0.00378 -0.1395 0.3517 0.6245
4.250 0.9585 0.01018 0.00405 -0.1381 0.3218 0.6266
4.500 0.9777 0.01060 0.00434 -0.1366 0.2905 0.6288
4.750 0.9973 0.01102 0.00463 -0.1353 0.2620 0.6308
5.000 1.0168 0.01144 0.00494 -0.1339 0.2347 0.6329
5.250 1.0357 0.01190 0.00529 -0.1325 0.2063 0.6350
5.500 1.0535 0.01244 0.00568 -0.1309 0.1739 0.6372
5.750 1.0739 0.01283 0.00601 -0.1297 0.1551 0.6394
6.000 1.0928 0.01333 0.00640 -0.1283 0.1316 0.6416
6.250 1.1109 0.01387 0.00682 -0.1268 0.1076 0.6437
6.500 1.1302 0.01434 0.00723 -0.1255 0.0913 0.6458
6.750 1.1495 0.01481 0.00764 -0.1243 0.0760 0.6479
7.000 1.1691 0.01527 0.00807 -0.1231 0.0641 0.6502
7.250 1.1885 0.01575 0.00852 -0.1218 0.0540 0.6525
7.500 1.2074 0.01624 0.00898 -0.1205 0.0451 0.6548
7.750 1.2265 0.01673 0.00945 -0.1193 0.0375 0.6570
8.000 1.2454 0.01724 0.00995 -0.1180 0.0307 0.6592
8.250 1.2635 0.01781 0.01050 -0.1166 0.0245 0.6613
8.500 1.2821 0.01833 0.01104 -0.1154 0.0209 0.6636
8.750 1.3001 0.01890 0.01162 -0.1140 0.0172 0.6661
9.000 1.3185 0.01944 0.01218 -0.1128 0.0149 0.6686
9.250 1.3357 0.02007 0.01282 -0.1114 0.0125 0.6711
9.500 1.3535 0.02064 0.01343 -0.1101 0.0110 0.6734
9.750 1.3707 0.02128 0.01408 -0.1087 0.0096 0.6756
10.000 1.3868 0.02198 0.01483 -0.1072 0.0081 0.6779
10.250 1.4040 0.02261 0.01552 -0.1059 0.0075 0.6805
10.500 1.4205 0.02330 0.01625 -0.1046 0.0066 0.6834
10.750 1.4356 0.02408 0.01707 -0.1031 0.0057 0.6862
11.000 1.4509 0.02487 0.01791 -0.1016 0.0050 0.6887
11.250 1.4662 0.02566 0.01875 -0.1002 0.0044 0.6911
11.500 1.4802 0.02655 0.01968 -0.0987 0.0038 0.6937
11.750 1.4937 0.02750 0.02069 -0.0971 0.0032 0.6965
12.000 1.5072 0.02844 0.02171 -0.0956 0.0029 0.6996
12.250 1.5202 0.02944 0.02277 -0.0941 0.0025 0.7028
12.500 1.5319 0.03054 0.02394 -0.0925 0.0022 0.7056
12.750 1.5433 0.03170 0.02517 -0.0909 0.0020 0.7087
13.000 1.5534 0.03298 0.02653 -0.0893 0.0018 0.7118
13.250 1.5644 0.03421 0.02785 -0.0878 0.0017 0.7151
13.500 1.5741 0.03556 0.02928 -0.0863 0.0016 0.7182
13.750 1.5834 0.03698 0.03079 -0.0848 0.0015 0.7215
14.000 1.5920 0.03851 0.03242 -0.0833 0.0014 0.7254
14.250 1.5995 0.04017 0.03416 -0.0819 0.0013 0.7294
14.500 1.6063 0.04194 0.03604 -0.0805 0.0012 0.7333
14.750 1.6121 0.04385 0.03805 -0.0792 0.0012 0.7372
15.000 1.6171 0.04589 0.04020 -0.0779 0.0011 0.7414
15.250 1.6208 0.04814 0.04256 -0.0767 0.0010 0.7457
15.500 1.6235 0.05058 0.04511 -0.0757 0.0010 0.7498
15.750 1.6245 0.05329 0.04796 -0.0747 0.0009 0.7547
16.000 1.6236 0.05631 0.05111 -0.0739 0.0009 0.7600
16.250 1.6234 0.05935 0.05428 -0.0734 0.0009 0.7653
16.500 1.6229 0.06255 0.05761 -0.0730 0.0008 0.7715
16.750 1.6212 0.06602 0.06122 -0.0729 0.0008 0.7776
17.000 1.6186 0.06976 0.06509 -0.0731 0.0008 0.7843
17.500 1.6088 0.07830 0.07393 -0.0743 0.0008 0.7981
18.000 1.5937 0.08837 0.08432 -0.0771 0.0008 0.8143
18.250 1.5837 0.09411 0.09023 -0.0791 0.0008 0.8235
18.500 1.5720 0.10030 0.09658 -0.0816 0.0008 0.8339
18.750 1.5592 0.10692 0.10339 -0.0845 0.0008 0.8458
19.000 1.5439 0.11421 0.11086 -0.0881 0.0008 0.8599
19.250 1.5281 0.12169 0.11854 -0.0920 0.0008 0.8785
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