EPPLER 399 AIRFOIL (e399-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 399 AIRFOIL (e399-il) Reynolds number: 500,000 Max Cl/Cd: 127.73 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e399-il-500000.txt Download as CSV file: xf-e399-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.4724 0.10651 0.10395 -0.0630 1.0000 0.0100
-14.250 -0.5080 0.09583 0.09315 -0.0678 1.0000 0.0098
-14.000 -0.5358 0.08743 0.08464 -0.0716 1.0000 0.0096
-13.750 -0.5609 0.08020 0.07730 -0.0748 1.0000 0.0095
-13.500 -0.5831 0.07422 0.07124 -0.0770 1.0000 0.0093
-13.250 -0.6069 0.06902 0.06597 -0.0783 1.0000 0.0093
-13.000 -0.6159 0.06187 0.05867 -0.0855 0.9980 0.0093
-12.750 -0.6162 0.05516 0.05177 -0.0938 0.9946 0.0091
-12.500 -0.6138 0.04906 0.04551 -0.1016 0.9901 0.0093
-12.250 -0.6056 0.04365 0.03993 -0.1095 0.9849 0.0094
-12.000 -0.5967 0.03880 0.03492 -0.1164 0.9777 0.0093
-11.750 -0.5812 0.03437 0.03032 -0.1239 0.9708 0.0095
-11.500 -0.5696 0.03050 0.02628 -0.1297 0.9590 0.0097
-11.250 -0.5517 0.02698 0.02257 -0.1361 0.9472 0.0099
-11.000 -0.5194 0.02429 0.01965 -0.1432 0.9401 0.0102
-10.750 -0.4916 0.02180 0.01699 -0.1481 0.9307 0.0106
-10.500 -0.4640 0.02025 0.01533 -0.1509 0.9197 0.0113
-10.250 -0.4358 0.01907 0.01399 -0.1530 0.9089 0.0121
-10.000 -0.4101 0.01802 0.01275 -0.1541 0.8973 0.0129
-9.750 -0.3892 0.01698 0.01160 -0.1544 0.8848 0.0139
-9.500 -0.3650 0.01629 0.01077 -0.1546 0.8743 0.0155
-9.250 -0.3412 0.01544 0.00981 -0.1549 0.8643 0.0179
-9.000 -0.3180 0.01474 0.00902 -0.1548 0.8540 0.0208
-8.750 -0.2926 0.01417 0.00837 -0.1550 0.8451 0.0255
-8.500 -0.2675 0.01370 0.00782 -0.1550 0.8359 0.0306
-8.250 -0.2412 0.01329 0.00735 -0.1551 0.8280 0.0362
-8.000 -0.2152 0.01291 0.00693 -0.1551 0.8196 0.0421
-7.750 -0.1883 0.01258 0.00653 -0.1553 0.8122 0.0485
-7.500 -0.1620 0.01223 0.00616 -0.1554 0.8040 0.0556
-7.250 -0.1346 0.01191 0.00579 -0.1556 0.7971 0.0635
-7.000 -0.1078 0.01159 0.00547 -0.1557 0.7896 0.0726
-6.750 -0.0803 0.01131 0.00515 -0.1559 0.7830 0.0829
-6.500 -0.0527 0.01103 0.00486 -0.1561 0.7764 0.0939
-6.250 -0.0251 0.01077 0.00459 -0.1563 0.7695 0.1061
-6.000 0.0030 0.01057 0.00434 -0.1565 0.7635 0.1196
-5.750 0.0308 0.01034 0.00413 -0.1567 0.7569 0.1339
-5.500 0.0590 0.01016 0.00392 -0.1569 0.7510 0.1488
-5.250 0.0874 0.01000 0.00375 -0.1572 0.7455 0.1646
-5.000 0.1155 0.00983 0.00359 -0.1574 0.7394 0.1810
-4.750 0.1439 0.00970 0.00344 -0.1576 0.7338 0.1983
-4.500 0.1725 0.00959 0.00333 -0.1579 0.7285 0.2161
-4.250 0.2008 0.00947 0.00322 -0.1581 0.7230 0.2339
-4.000 0.2294 0.00940 0.00313 -0.1583 0.7178 0.2514
-3.750 0.2582 0.00935 0.00306 -0.1585 0.7129 0.2687
-3.500 0.2866 0.00927 0.00300 -0.1587 0.7077 0.2855
-3.250 0.3152 0.00922 0.00294 -0.1589 0.7029 0.3017
-3.000 0.3442 0.00922 0.00290 -0.1592 0.6984 0.3172
-2.750 0.3726 0.00916 0.00288 -0.1594 0.6936 0.3320
-2.500 0.4011 0.00912 0.00285 -0.1596 0.6888 0.3464
-2.250 0.4299 0.00912 0.00282 -0.1598 0.6845 0.3605
-2.000 0.4588 0.00914 0.00281 -0.1600 0.6802 0.3744
-1.750 0.4871 0.00912 0.00281 -0.1602 0.6757 0.3884
-1.500 0.5157 0.00910 0.00281 -0.1604 0.6713 0.4027
-1.250 0.5445 0.00912 0.00282 -0.1606 0.6673 0.4171
-1.000 0.5732 0.00914 0.00285 -0.1608 0.6632 0.4314
-0.750 0.6015 0.00913 0.00288 -0.1610 0.6589 0.4464
-0.500 0.6299 0.00913 0.00291 -0.1611 0.6548 0.4619
-0.250 0.6587 0.00917 0.00293 -0.1613 0.6509 0.4780
0.000 0.6873 0.00922 0.00300 -0.1616 0.6470 0.4947
0.250 0.7154 0.00921 0.00306 -0.1617 0.6429 0.5119
0.500 0.7437 0.00922 0.00312 -0.1618 0.6388 0.5298
0.750 0.7721 0.00926 0.00317 -0.1620 0.6350 0.5483
1.000 0.8008 0.00933 0.00327 -0.1622 0.6312 0.5677
1.250 0.8285 0.00934 0.00336 -0.1622 0.6271 0.5876
1.500 0.8564 0.00936 0.00345 -0.1623 0.6230 0.6084
1.750 0.8845 0.00941 0.00352 -0.1624 0.6191 0.6300
2.000 0.9129 0.00950 0.00364 -0.1625 0.6152 0.6517
2.250 0.9400 0.00951 0.00377 -0.1624 0.6111 0.6743
2.500 0.9673 0.00954 0.00387 -0.1623 0.6068 0.6980
2.750 0.9946 0.00958 0.00397 -0.1623 0.6027 0.7215
3.000 1.0222 0.00968 0.00412 -0.1622 0.5986 0.7469
3.250 1.0480 0.00969 0.00425 -0.1618 0.5942 0.7729
3.500 1.0738 0.00971 0.00437 -0.1614 0.5896 0.8008
3.750 1.0992 0.00977 0.00448 -0.1609 0.5852 0.8315
4.000 1.1224 0.00980 0.00462 -0.1599 0.5806 0.8664
4.250 1.1405 0.00972 0.00469 -0.1576 0.5755 0.9163
4.500 1.1656 0.00970 0.00470 -0.1571 0.5703 1.0000
4.750 1.1932 0.00985 0.00483 -0.1572 0.5649 1.0000
5.000 1.2195 0.00994 0.00496 -0.1570 0.5589 1.0000
5.250 1.2462 0.01008 0.00508 -0.1569 0.5530 1.0000
5.500 1.2722 0.01021 0.00524 -0.1567 0.5470 1.0000
5.750 1.2975 0.01032 0.00538 -0.1563 0.5402 1.0000
6.000 1.3229 0.01050 0.00553 -0.1559 0.5336 1.0000
6.250 1.3473 0.01060 0.00570 -0.1554 0.5258 1.0000
6.500 1.3714 0.01080 0.00586 -0.1548 0.5182 1.0000
6.750 1.3948 0.01092 0.00606 -0.1540 0.5091 1.0000
7.000 1.4174 0.01112 0.00625 -0.1532 0.5001 1.0000
7.250 1.4393 0.01132 0.00646 -0.1521 0.4898 1.0000
7.500 1.4604 0.01153 0.00670 -0.1510 0.4785 1.0000
7.750 1.4800 0.01179 0.00696 -0.1496 0.4663 1.0000
8.000 1.4972 0.01209 0.00724 -0.1477 0.4530 1.0000
8.250 1.5114 0.01244 0.00757 -0.1452 0.4374 1.0000
8.500 1.5240 0.01286 0.00796 -0.1426 0.4196 1.0000
8.750 1.5339 0.01339 0.00843 -0.1395 0.3983 1.0000
9.000 1.5407 0.01409 0.00903 -0.1361 0.3755 1.0000
9.250 1.5467 0.01488 0.00973 -0.1326 0.3501 1.0000
9.500 1.5506 0.01582 0.01058 -0.1290 0.3260 1.0000
9.750 1.5528 0.01692 0.01156 -0.1254 0.3009 1.0000
10.000 1.5542 0.01814 0.01269 -0.1219 0.2766 1.0000
10.250 1.5538 0.01957 0.01401 -0.1184 0.2529 1.0000
10.500 1.5537 0.02109 0.01544 -0.1152 0.2298 1.0000
10.750 1.5528 0.02279 0.01704 -0.1121 0.2082 1.0000
11.000 1.5520 0.02460 0.01877 -0.1093 0.1882 1.0000
11.250 1.5512 0.02652 0.02062 -0.1068 0.1686 1.0000
11.500 1.5504 0.02855 0.02258 -0.1045 0.1511 1.0000
11.750 1.5495 0.03070 0.02466 -0.1023 0.1350 1.0000
12.250 1.5484 0.03522 0.02909 -0.0987 0.1064 1.0000
12.500 1.5483 0.03759 0.03143 -0.0971 0.0942 1.0000
12.750 1.5480 0.04007 0.03387 -0.0957 0.0828 1.0000
13.000 1.5480 0.04260 0.03638 -0.0945 0.0726 1.0000
13.250 1.5485 0.04518 0.03894 -0.0934 0.0636 1.0000
13.500 1.5494 0.04779 0.04156 -0.0925 0.0558 1.0000
13.750 1.5497 0.05053 0.04431 -0.0917 0.0488 1.0000
14.000 1.5504 0.05333 0.04712 -0.0910 0.0431 1.0000
14.250 1.5502 0.05629 0.05009 -0.0904 0.0381 1.0000
14.500 1.5507 0.05926 0.05309 -0.0899 0.0339 1.0000
14.750 1.5516 0.06225 0.05613 -0.0896 0.0303 1.0000
15.000 1.5507 0.06552 0.05945 -0.0893 0.0273 1.0000
15.250 1.5519 0.06861 0.06259 -0.0892 0.0247 1.0000
15.500 1.5515 0.07197 0.06601 -0.0892 0.0224 1.0000
15.750 1.5514 0.07536 0.06945 -0.0893 0.0205 1.0000
16.000 1.5508 0.07888 0.07304 -0.0895 0.0187 1.0000
16.250 1.5506 0.08242 0.07666 -0.0899 0.0172 1.0000
16.500 1.5477 0.08640 0.08072 -0.0904 0.0159 1.0000
16.750 1.5484 0.08991 0.08431 -0.0909 0.0146 1.0000
17.000 1.5430 0.09441 0.08887 -0.0917 0.0136 1.0000
17.250 1.5429 0.09815 0.09272 -0.0925 0.0125 1.0000
17.500 1.5414 0.10215 0.09680 -0.0934 0.0116 1.0000
17.750 1.5336 0.10721 0.10193 -0.0947 0.0109 1.0000
18.000 1.5337 0.11106 0.10590 -0.0958 0.0102 1.0000
18.250 1.5314 0.11532 0.11026 -0.0971 0.0095 1.0000
18.500 1.5262 0.12012 0.11514 -0.0988 0.0090 1.0000
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Polar data table (+)
Polar graphs
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