EPPLER 417 AIRFOIL (e417-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 417 AIRFOIL (e417-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.47 at α=1° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e417-il-1000000-n5.txt Download as CSV file: xf-e417-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 417 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5639 0.07556 0.07326 -0.1105 0.9854 0.0051
-14.500 -0.6043 0.06614 0.06363 -0.1139 0.9818 0.0050
-14.250 -0.6276 0.05855 0.05584 -0.1186 0.9801 0.0050
-14.000 -0.6243 0.05527 0.05249 -0.1212 0.9790 0.0051
-13.750 -0.6455 0.04867 0.04563 -0.1251 0.9777 0.0050
-13.500 -0.6588 0.04354 0.04025 -0.1278 0.9766 0.0050
-13.250 -0.6514 0.04118 0.03780 -0.1298 0.9759 0.0050
-13.000 -0.6469 0.03835 0.03484 -0.1318 0.9753 0.0050
-12.750 -0.6392 0.03585 0.03220 -0.1338 0.9747 0.0051
-12.500 -0.6475 0.03384 0.03006 -0.1314 0.9699 0.0051
-12.250 -0.6415 0.03184 0.02792 -0.1317 0.9679 0.0051
-12.000 -0.6294 0.03024 0.02623 -0.1325 0.9665 0.0052
-11.750 -0.6156 0.02860 0.02447 -0.1335 0.9654 0.0053
-11.500 -0.6004 0.02690 0.02265 -0.1345 0.9644 0.0053
-11.250 -0.5805 0.02573 0.02139 -0.1359 0.9637 0.0054
-11.000 -0.5620 0.02419 0.01971 -0.1369 0.9630 0.0054
-10.750 -0.5549 0.02351 0.01898 -0.1349 0.9593 0.0056
-10.500 -0.5437 0.02259 0.01798 -0.1337 0.9562 0.0057
-10.250 -0.5254 0.02148 0.01678 -0.1339 0.9545 0.0058
-10.000 -0.5047 0.02042 0.01562 -0.1344 0.9532 0.0058
-9.750 -0.4826 0.01940 0.01452 -0.1351 0.9522 0.0059
-9.500 -0.4591 0.01849 0.01354 -0.1360 0.9512 0.0059
-9.250 -0.4358 0.01761 0.01258 -0.1368 0.9502 0.0063
-9.000 -0.4396 0.01710 0.01204 -0.1319 0.9444 0.0063
-8.750 -0.4208 0.01635 0.01122 -0.1317 0.9420 0.0064
-8.500 -0.3982 0.01555 0.01035 -0.1324 0.9404 0.0065
-8.250 -0.3720 0.01492 0.00967 -0.1335 0.9392 0.0067
-8.000 -0.3446 0.01434 0.00904 -0.1347 0.9381 0.0069
-7.750 -0.3159 0.01379 0.00844 -0.1361 0.9371 0.0069
-7.500 -0.2954 0.01299 0.00758 -0.1361 0.9351 0.0072
-7.250 -0.2853 0.01253 0.00708 -0.1333 0.9310 0.0074
-7.000 -0.2613 0.01204 0.00656 -0.1334 0.9290 0.0076
-6.750 -0.2341 0.01163 0.00613 -0.1341 0.9276 0.0079
-6.500 -0.2054 0.01122 0.00569 -0.1351 0.9263 0.0081
-6.250 -0.1756 0.01086 0.00529 -0.1362 0.9253 0.0084
-6.000 -0.1452 0.01052 0.00493 -0.1374 0.9243 0.0088
-5.750 -0.1138 0.01022 0.00461 -0.1387 0.9234 0.0094
-5.500 -0.0817 0.00995 0.00431 -0.1402 0.9226 0.0098
-5.250 -0.0594 0.00973 0.00407 -0.1394 0.9203 0.0101
-5.000 -0.0369 0.00951 0.00383 -0.1387 0.9178 0.0108
-4.750 -0.0099 0.00930 0.00361 -0.1389 0.9158 0.0117
-4.500 0.0193 0.00910 0.00339 -0.1396 0.9142 0.0129
-4.250 0.0497 0.00890 0.00319 -0.1405 0.9128 0.0166
-4.000 0.0820 0.00822 0.00282 -0.1425 0.9115 0.0956
-3.750 0.1165 0.00739 0.00242 -0.1452 0.9102 0.2200
-3.500 0.1547 0.00630 0.00194 -0.1491 0.9090 0.3992
-3.250 0.1851 0.00586 0.00180 -0.1503 0.9065 0.4931
-3.000 0.2103 0.00575 0.00179 -0.1499 0.9027 0.5282
-2.750 0.2392 0.00571 0.00177 -0.1503 0.8996 0.5506
-2.500 0.2703 0.00566 0.00173 -0.1511 0.8970 0.5607
-2.250 0.3040 0.00563 0.00165 -0.1525 0.8947 0.5652
-2.000 0.3286 0.00561 0.00164 -0.1519 0.8904 0.5682
-1.750 0.3549 0.00558 0.00161 -0.1516 0.8855 0.5710
-1.500 0.3875 0.00553 0.00153 -0.1528 0.8811 0.5737
-1.250 0.4130 0.00553 0.00152 -0.1523 0.8751 0.5764
-1.000 0.4416 0.00551 0.00148 -0.1526 0.8695 0.5787
-0.750 0.4727 0.00550 0.00144 -0.1534 0.8655 0.5809
-0.500 0.4984 0.00550 0.00146 -0.1530 0.8601 0.5832
-0.250 0.5278 0.00549 0.00144 -0.1535 0.8532 0.5854
0.000 0.5547 0.00550 0.00144 -0.1533 0.8427 0.5876
0.250 0.5823 0.00552 0.00142 -0.1533 0.8278 0.5900
0.500 0.6090 0.00558 0.00141 -0.1531 0.8115 0.5923
0.750 0.6342 0.00567 0.00143 -0.1526 0.7916 0.5943
1.000 0.6557 0.00583 0.00147 -0.1512 0.7632 0.5962
1.250 0.6723 0.00608 0.00156 -0.1488 0.7248 0.5983
1.500 0.6840 0.00638 0.00169 -0.1453 0.6834 0.6004
1.750 0.6960 0.00672 0.00186 -0.1420 0.6423 0.6024
2.000 0.7117 0.00704 0.00203 -0.1395 0.6048 0.6044
2.250 0.7289 0.00738 0.00221 -0.1373 0.5678 0.6066
2.500 0.7471 0.00774 0.00241 -0.1355 0.5287 0.6087
2.750 0.7626 0.00826 0.00267 -0.1331 0.4733 0.6105
3.000 0.7785 0.00883 0.00296 -0.1310 0.4089 0.6123
3.250 0.7981 0.00928 0.00321 -0.1295 0.3618 0.6141
3.500 0.8173 0.00978 0.00349 -0.1281 0.3096 0.6161
3.750 0.8350 0.01043 0.00384 -0.1264 0.2453 0.6182
4.000 0.8549 0.01095 0.00414 -0.1251 0.1983 0.6204
4.250 0.8746 0.01150 0.00447 -0.1239 0.1519 0.6224
4.500 0.8954 0.01199 0.00479 -0.1227 0.1171 0.6241
4.750 0.9159 0.01248 0.00513 -0.1216 0.0852 0.6257
5.000 0.9366 0.01297 0.00549 -0.1205 0.0569 0.6275
5.250 0.9561 0.01356 0.00593 -0.1191 0.0277 0.6295
5.500 0.9763 0.01410 0.00638 -0.1179 0.0104 0.6316
5.750 0.9989 0.01444 0.00674 -0.1171 0.0087 0.6337
6.000 1.0216 0.01474 0.00707 -0.1163 0.0081 0.6357
6.250 1.0442 0.01506 0.00742 -0.1155 0.0077 0.6376
6.500 1.0663 0.01541 0.00779 -0.1146 0.0074 0.6394
6.750 1.0879 0.01578 0.00819 -0.1137 0.0070 0.6410
7.000 1.1091 0.01618 0.00864 -0.1126 0.0067 0.6430
7.250 1.1299 0.01661 0.00912 -0.1116 0.0064 0.6451
7.500 1.1495 0.01715 0.00971 -0.1103 0.0060 0.6471
7.750 1.1692 0.01767 0.01028 -0.1090 0.0058 0.6492
8.000 1.1895 0.01813 0.01079 -0.1079 0.0057 0.6512
8.250 1.2091 0.01861 0.01132 -0.1067 0.0055 0.6531
8.500 1.2281 0.01914 0.01190 -0.1054 0.0054 0.6550
9.000 1.2648 0.02032 0.01319 -0.1027 0.0051 0.6589
9.250 1.2822 0.02095 0.01390 -0.1012 0.0050 0.6610
9.500 1.2988 0.02164 0.01465 -0.0996 0.0048 0.6631
9.750 1.3152 0.02235 0.01542 -0.0980 0.0047 0.6652
10.000 1.3308 0.02311 0.01625 -0.0963 0.0046 0.6673
10.250 1.3458 0.02390 0.01710 -0.0946 0.0045 0.6693
10.500 1.3602 0.02475 0.01802 -0.0928 0.0045 0.6712
10.750 1.3744 0.02561 0.01895 -0.0911 0.0044 0.6733
11.000 1.3876 0.02653 0.01996 -0.0893 0.0043 0.6756
11.250 1.3999 0.02755 0.02105 -0.0874 0.0042 0.6779
11.500 1.4107 0.02867 0.02226 -0.0853 0.0041 0.6801
11.750 1.4200 0.02994 0.02362 -0.0832 0.0041 0.6822
12.000 1.4268 0.03141 0.02519 -0.0809 0.0040 0.6843
12.250 1.4293 0.03331 0.02721 -0.0781 0.0039 0.6862
12.750 1.4399 0.03672 0.03086 -0.0738 0.0038 0.6902
13.000 1.4475 0.03825 0.03249 -0.0720 0.0038 0.6927
13.250 1.4534 0.03997 0.03433 -0.0703 0.0038 0.6953
13.500 1.4582 0.04184 0.03631 -0.0686 0.0037 0.6978
13.750 1.4616 0.04389 0.03848 -0.0669 0.0037 0.7002
14.000 1.4639 0.04614 0.04085 -0.0654 0.0037 0.7023
14.250 1.4655 0.04855 0.04339 -0.0640 0.0036 0.7045
14.500 1.4658 0.05118 0.04616 -0.0628 0.0036 0.7068
14.750 1.4647 0.05410 0.04921 -0.0619 0.0036 0.7093
15.000 1.4624 0.05730 0.05255 -0.0611 0.0035 0.7119
15.250 1.4584 0.06085 0.05625 -0.0607 0.0035 0.7145
15.500 1.4534 0.06471 0.06024 -0.0606 0.0035 0.7170
15.750 1.4472 0.06893 0.06463 -0.0610 0.0035 0.7194
16.000 1.4393 0.07364 0.06950 -0.0618 0.0034 0.7219
16.250 1.4304 0.07876 0.07477 -0.0631 0.0034 0.7244
16.500 1.4198 0.08439 0.08056 -0.0649 0.0034 0.7268
16.750 1.4081 0.09047 0.08681 -0.0673 0.0034 0.7290
17.000 1.3948 0.09714 0.09363 -0.0702 0.0034 0.7310
17.250 1.3811 0.10417 0.10082 -0.0737 0.0034 0.7329
17.500 1.3669 0.11159 0.10840 -0.0777 0.0034 0.7347
17.750 1.3515 0.11948 0.11645 -0.0822 0.0033 0.7366
18.000 1.3360 0.12762 0.12475 -0.0870 0.0033 0.7384
18.250 1.3192 0.13630 0.13357 -0.0924 0.0033 0.7403
18.500 1.3020 0.14526 0.14269 -0.0981 0.0033 0.7420
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Polar data table (+)
Polar graphs
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