EPPLER 399 AIRFOIL (e399-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 399 AIRFOIL (e399-il) Reynolds number: 1,000,000 Max Cl/Cd: 142.43 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e399-il-1000000-n5.txt Download as CSV file: xf-e399-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 399 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 -0.6102 0.08648 0.08382 -0.0790 0.9976 0.0034
-15.000 -0.6276 0.07837 0.07561 -0.0853 0.9962 0.0033
-14.750 -0.6482 0.06992 0.06703 -0.0920 0.9942 0.0032
-14.500 -0.6814 0.06031 0.05727 -0.0994 0.9911 0.0033
-14.250 -0.7041 0.05223 0.04906 -0.1063 0.9866 0.0033
-14.000 -0.7195 0.04517 0.04186 -0.1131 0.9806 0.0032
-13.750 -0.7380 0.03891 0.03546 -0.1179 0.9645 0.0032
-13.500 -0.7275 0.03312 0.02949 -0.1272 0.9507 0.0032
-13.250 -0.6923 0.02752 0.02367 -0.1412 0.9395 0.0033
-13.000 -0.6527 0.02357 0.01947 -0.1530 0.9185 0.0034
-12.750 -0.6468 0.02146 0.01710 -0.1552 0.8845 0.0034
-12.500 -0.6398 0.02018 0.01562 -0.1549 0.8635 0.0035
-12.250 -0.6269 0.01926 0.01456 -0.1543 0.8480 0.0036
-12.000 -0.6110 0.01844 0.01360 -0.1538 0.8355 0.0036
-11.750 -0.5931 0.01771 0.01275 -0.1534 0.8246 0.0037
-11.500 -0.5738 0.01704 0.01196 -0.1530 0.8138 0.0039
-11.250 -0.5527 0.01642 0.01124 -0.1528 0.8039 0.0040
-11.000 -0.5308 0.01587 0.01057 -0.1526 0.7949 0.0041
-10.750 -0.5076 0.01535 0.00996 -0.1525 0.7866 0.0043
-10.500 -0.4846 0.01479 0.00930 -0.1523 0.7789 0.0045
-10.250 -0.4605 0.01426 0.00869 -0.1523 0.7711 0.0049
-10.000 -0.4361 0.01382 0.00816 -0.1522 0.7632 0.0053
-9.750 -0.4106 0.01341 0.00768 -0.1523 0.7558 0.0057
-9.500 -0.3851 0.01304 0.00723 -0.1523 0.7485 0.0062
-9.250 -0.3590 0.01262 0.00676 -0.1524 0.7424 0.0071
-9.000 -0.3326 0.01229 0.00637 -0.1525 0.7355 0.0080
-8.750 -0.3062 0.01194 0.00596 -0.1526 0.7292 0.0096
-8.500 -0.2792 0.01161 0.00560 -0.1528 0.7226 0.0113
-8.250 -0.2524 0.01132 0.00526 -0.1529 0.7160 0.0136
-8.000 -0.2250 0.01103 0.00493 -0.1531 0.7106 0.0163
-7.750 -0.1974 0.01076 0.00463 -0.1533 0.7049 0.0194
-7.500 -0.1699 0.01052 0.00436 -0.1534 0.6991 0.0230
-7.250 -0.1420 0.01028 0.00410 -0.1537 0.6940 0.0269
-7.000 -0.1140 0.01005 0.00385 -0.1539 0.6881 0.0317
-6.750 -0.0863 0.00983 0.00362 -0.1541 0.6825 0.0381
-6.500 -0.0580 0.00958 0.00339 -0.1544 0.6780 0.0465
-6.250 -0.0296 0.00936 0.00318 -0.1547 0.6731 0.0560
-6.000 -0.0014 0.00917 0.00300 -0.1549 0.6680 0.0651
-5.750 0.0269 0.00901 0.00283 -0.1552 0.6633 0.0738
-5.500 0.0556 0.00883 0.00267 -0.1555 0.6586 0.0838
-5.250 0.0842 0.00868 0.00252 -0.1557 0.6539 0.0944
-5.000 0.1126 0.00856 0.00239 -0.1560 0.6494 0.1046
-4.750 0.1415 0.00843 0.00227 -0.1563 0.6453 0.1151
-4.500 0.1703 0.00832 0.00217 -0.1565 0.6408 0.1258
-4.250 0.1990 0.00821 0.00207 -0.1568 0.6363 0.1385
-3.750 0.2566 0.00801 0.00190 -0.1574 0.6287 0.1664
-3.500 0.2855 0.00792 0.00183 -0.1577 0.6244 0.1797
-3.250 0.3143 0.00785 0.00177 -0.1579 0.6202 0.1937
-3.000 0.3428 0.00779 0.00172 -0.1581 0.6164 0.2085
-2.750 0.3718 0.00772 0.00168 -0.1584 0.6129 0.2232
-2.500 0.4008 0.00767 0.00165 -0.1587 0.6090 0.2373
-2.250 0.4296 0.00763 0.00162 -0.1590 0.6051 0.2514
-2.000 0.4581 0.00761 0.00161 -0.1592 0.6013 0.2658
-1.750 0.4869 0.00758 0.00160 -0.1594 0.5979 0.2784
-1.500 0.5159 0.00755 0.00159 -0.1597 0.5944 0.2912
-1.000 0.5731 0.00754 0.00160 -0.1601 0.5869 0.3153
-0.750 0.6014 0.00755 0.00162 -0.1602 0.5831 0.3272
-0.500 0.6303 0.00754 0.00164 -0.1605 0.5800 0.3384
-0.250 0.6590 0.00754 0.00166 -0.1607 0.5764 0.3503
0.000 0.6875 0.00755 0.00169 -0.1609 0.5726 0.3628
0.250 0.7156 0.00758 0.00172 -0.1610 0.5688 0.3748
0.500 0.7440 0.00760 0.00176 -0.1611 0.5654 0.3869
0.750 0.7727 0.00760 0.00181 -0.1613 0.5619 0.4000
1.000 0.8011 0.00762 0.00185 -0.1615 0.5580 0.4129
1.250 0.8290 0.00766 0.00191 -0.1616 0.5539 0.4258
1.500 0.8569 0.00770 0.00197 -0.1617 0.5501 0.4397
1.750 0.8854 0.00771 0.00204 -0.1619 0.5463 0.4543
2.000 0.9135 0.00774 0.00211 -0.1620 0.5420 0.4688
2.250 0.9411 0.00780 0.00219 -0.1620 0.5374 0.4841
2.500 0.9688 0.00785 0.00227 -0.1621 0.5332 0.4996
2.750 0.9968 0.00788 0.00235 -0.1622 0.5285 0.5158
3.000 1.0242 0.00794 0.00245 -0.1622 0.5231 0.5328
3.250 1.0512 0.00802 0.00256 -0.1621 0.5178 0.5495
3.500 1.0788 0.00806 0.00265 -0.1621 0.5119 0.5664
3.750 1.1053 0.00816 0.00278 -0.1620 0.5048 0.5845
4.000 1.1323 0.00823 0.00290 -0.1619 0.4979 0.6027
4.250 1.1585 0.00834 0.00303 -0.1617 0.4896 0.6206
4.500 1.1848 0.00844 0.00317 -0.1615 0.4819 0.6406
4.750 1.2102 0.00857 0.00332 -0.1611 0.4725 0.6603
5.000 1.2360 0.00869 0.00349 -0.1608 0.4628 0.6807
5.250 1.2605 0.00885 0.00367 -0.1603 0.4518 0.7029
5.500 1.2843 0.00905 0.00388 -0.1597 0.4391 0.7254
6.000 1.3299 0.00949 0.00435 -0.1580 0.4090 0.7772
6.250 1.3506 0.00977 0.00464 -0.1568 0.3913 0.8075
6.500 1.3696 0.01007 0.00495 -0.1553 0.3713 0.8435
6.750 1.3846 0.01037 0.00527 -0.1528 0.3509 0.8951
7.000 1.3947 0.01069 0.00558 -0.1494 0.3295 1.0000
7.250 1.4082 0.01121 0.00599 -0.1469 0.3046 1.0000
7.750 1.4318 0.01240 0.00694 -0.1415 0.2577 1.0000
8.000 1.4413 0.01310 0.00752 -0.1385 0.2335 1.0000
8.250 1.4488 0.01390 0.00819 -0.1353 0.2081 1.0000
8.500 1.4561 0.01473 0.00890 -0.1322 0.1846 1.0000
8.750 1.4622 0.01565 0.00971 -0.1290 0.1630 1.0000
9.000 1.4705 0.01651 0.01050 -0.1263 0.1469 1.0000
9.250 1.4789 0.01741 0.01134 -0.1237 0.1322 1.0000
9.500 1.4871 0.01837 0.01225 -0.1212 0.1193 1.0000
9.750 1.4940 0.01945 0.01328 -0.1187 0.1059 1.0000
10.000 1.5007 0.02060 0.01438 -0.1163 0.0939 1.0000
10.250 1.5068 0.02186 0.01560 -0.1139 0.0824 1.0000
10.500 1.5119 0.02325 0.01694 -0.1116 0.0708 1.0000
10.750 1.5176 0.02467 0.01833 -0.1096 0.0616 1.0000
11.250 1.5280 0.02778 0.02139 -0.1057 0.0451 1.0000
11.500 1.5336 0.02940 0.02300 -0.1041 0.0389 1.0000
11.750 1.5390 0.03110 0.02470 -0.1025 0.0332 1.0000
12.000 1.5452 0.03279 0.02639 -0.1011 0.0287 1.0000
12.250 1.5513 0.03454 0.02815 -0.0998 0.0248 1.0000
12.500 1.5563 0.03645 0.03008 -0.0985 0.0210 1.0000
12.750 1.5619 0.03836 0.03201 -0.0974 0.0181 1.0000
13.000 1.5673 0.04034 0.03401 -0.0963 0.0157 1.0000
13.250 1.5739 0.04226 0.03597 -0.0954 0.0141 1.0000
13.500 1.5796 0.04432 0.03807 -0.0946 0.0126 1.0000
13.750 1.5851 0.04645 0.04024 -0.0938 0.0113 1.0000
14.000 1.5915 0.04852 0.04236 -0.0932 0.0103 1.0000
14.250 1.5968 0.05077 0.04466 -0.0926 0.0093 1.0000
14.500 1.6020 0.05308 0.04701 -0.0921 0.0086 1.0000
14.750 1.6076 0.05537 0.04936 -0.0916 0.0078 1.0000
15.000 1.6118 0.05790 0.05193 -0.0912 0.0071 1.0000
15.250 1.6165 0.06039 0.05449 -0.0909 0.0064 1.0000
15.500 1.6206 0.06300 0.05716 -0.0907 0.0059 1.0000
15.750 1.6238 0.06579 0.06000 -0.0906 0.0054 1.0000
16.000 1.6277 0.06853 0.06280 -0.0905 0.0049 1.0000
16.250 1.6304 0.07147 0.06581 -0.0905 0.0045 1.0000
16.500 1.6330 0.07445 0.06885 -0.0906 0.0041 1.0000
16.750 1.6346 0.07764 0.07211 -0.0908 0.0038 1.0000
17.000 1.6368 0.08078 0.07532 -0.0911 0.0036 1.0000
17.250 1.6390 0.08398 0.07860 -0.0915 0.0033 1.0000
17.500 1.6395 0.08747 0.08216 -0.0920 0.0031 1.0000
17.750 1.6399 0.09098 0.08574 -0.0925 0.0029 1.0000
18.000 1.6395 0.09469 0.08952 -0.0932 0.0027 1.0000
18.250 1.6395 0.09837 0.09329 -0.0940 0.0025 1.0000
18.500 1.6399 0.10201 0.09701 -0.0949 0.0024 1.0000
18.750 1.6389 0.10591 0.10099 -0.0959 0.0023 1.0000
19.000 1.6375 0.10990 0.10506 -0.0970 0.0021 1.0000
19.250 1.6363 0.11386 0.10910 -0.0982 0.0020 1.0000
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Polar data table (+)
Polar graphs
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