EPPLER 399 AIRFOIL (e399-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 399 AIRFOIL (e399-il) Reynolds number: 200,000 Max Cl/Cd: 83.55 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e399-il-200000.txt Download as CSV file: xf-e399-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5136 0.06721 0.06358 -0.0851 0.9926 0.0223
-11.250 -0.5218 0.05831 0.05447 -0.0967 0.9851 0.0221
-11.000 -0.5267 0.05060 0.04647 -0.1081 0.9752 0.0220
-10.750 -0.5303 0.04433 0.03986 -0.1180 0.9625 0.0220
-10.500 -0.5265 0.03866 0.03361 -0.1272 0.9492 0.0223
-10.250 -0.5000 0.03552 0.03040 -0.1314 0.9449 0.0232
-10.000 -0.4786 0.03336 0.02807 -0.1339 0.9367 0.0244
-9.750 -0.4500 0.03058 0.02473 -0.1383 0.9316 0.0263
-9.500 -0.4137 0.02871 0.02291 -0.1421 0.9293 0.0289
-9.250 -0.3916 0.02668 0.02056 -0.1430 0.9208 0.0313
-9.000 -0.3578 0.02503 0.01887 -0.1456 0.9164 0.0344
-8.750 -0.3208 0.02342 0.01715 -0.1489 0.9132 0.0399
-8.500 -0.2980 0.02239 0.01605 -0.1491 0.9038 0.0453
-8.250 -0.2636 0.02120 0.01477 -0.1514 0.8991 0.0532
-8.000 -0.2358 0.02034 0.01383 -0.1523 0.8917 0.0613
-7.750 -0.2060 0.01952 0.01294 -0.1534 0.8847 0.0703
-7.500 -0.1729 0.01870 0.01203 -0.1551 0.8794 0.0804
-7.250 -0.1491 0.01809 0.01136 -0.1548 0.8703 0.0898
-7.000 -0.1170 0.01742 0.01060 -0.1560 0.8649 0.1016
-6.750 -0.0923 0.01701 0.01012 -0.1558 0.8565 0.1132
-6.500 -0.0625 0.01648 0.00953 -0.1565 0.8502 0.1272
-6.250 -0.0351 0.01606 0.00907 -0.1568 0.8433 0.1421
-6.000 -0.0078 0.01566 0.00867 -0.1569 0.8361 0.1581
-5.750 0.0232 0.01528 0.00825 -0.1578 0.8311 0.1762
-5.500 0.0480 0.01507 0.00805 -0.1575 0.8233 0.1936
-5.250 0.0774 0.01482 0.00776 -0.1580 0.8174 0.2132
-5.000 0.1064 0.01465 0.00752 -0.1583 0.8117 0.2334
-4.750 0.1328 0.01453 0.00738 -0.1582 0.8047 0.2527
-4.500 0.1627 0.01437 0.00722 -0.1587 0.7997 0.2725
-4.250 0.1905 0.01431 0.00714 -0.1588 0.7940 0.2917
-4.000 0.2176 0.01426 0.00708 -0.1588 0.7876 0.3104
-3.750 0.2477 0.01419 0.00694 -0.1592 0.7828 0.3296
-3.500 0.2753 0.01419 0.00692 -0.1592 0.7774 0.3474
-3.250 0.3022 0.01417 0.00691 -0.1591 0.7715 0.3645
-3.000 0.3319 0.01412 0.00681 -0.1595 0.7668 0.3821
-2.750 0.3604 0.01413 0.00679 -0.1596 0.7620 0.3987
-2.500 0.3866 0.01415 0.00684 -0.1594 0.7562 0.4147
-2.250 0.4155 0.01413 0.00680 -0.1596 0.7515 0.4312
-2.000 0.4462 0.01413 0.00674 -0.1601 0.7477 0.4479
-1.750 0.4710 0.01419 0.00687 -0.1597 0.7418 0.4637
-1.500 0.4987 0.01421 0.00689 -0.1597 0.7370 0.4802
-1.250 0.5285 0.01421 0.00687 -0.1600 0.7330 0.4975
-1.000 0.5562 0.01428 0.00696 -0.1600 0.7285 0.5145
-0.750 0.5820 0.01435 0.00709 -0.1598 0.7231 0.5317
-0.500 0.6103 0.01437 0.00713 -0.1598 0.7188 0.5499
-0.250 0.6406 0.01439 0.00714 -0.1602 0.7153 0.5690
0.000 0.6656 0.01452 0.00736 -0.1598 0.7101 0.5880
0.250 0.6920 0.01460 0.00750 -0.1596 0.7053 0.6081
0.500 0.7207 0.01464 0.00755 -0.1597 0.7013 0.6302
0.750 0.7508 0.01468 0.00761 -0.1600 0.6980 0.6516
1.000 0.7731 0.01484 0.00792 -0.1591 0.6924 0.6734
1.250 0.7993 0.01492 0.00807 -0.1588 0.6878 0.6978
1.500 0.8271 0.01494 0.00815 -0.1586 0.6840 0.7220
1.750 0.8541 0.01505 0.00830 -0.1583 0.6802 0.7486
2.000 0.8746 0.01519 0.00861 -0.1569 0.6747 0.7745
2.250 0.8985 0.01524 0.00873 -0.1559 0.6703 0.8036
2.500 0.9233 0.01523 0.00877 -0.1550 0.6667 0.8357
2.750 0.9409 0.01531 0.00897 -0.1527 0.6622 0.8729
3.000 0.9547 0.01528 0.00907 -0.1496 0.6568 0.9311
3.250 0.9898 0.01530 0.00907 -0.1513 0.6525 1.0000
3.500 1.0253 0.01543 0.00910 -0.1530 0.6489 1.0000
3.750 1.0489 0.01577 0.00951 -0.1527 0.6428 1.0000
4.000 1.0775 0.01594 0.00968 -0.1531 0.6377 1.0000
4.250 1.1099 0.01604 0.00971 -0.1540 0.6337 1.0000
4.500 1.1347 0.01633 0.01006 -0.1537 0.6280 1.0000
4.750 1.1608 0.01652 0.01028 -0.1536 0.6222 1.0000
5.000 1.1924 0.01658 0.01030 -0.1543 0.6176 1.0000
5.250 1.2165 0.01685 0.01063 -0.1538 0.6114 1.0000
5.500 1.2423 0.01698 0.01080 -0.1535 0.6050 1.0000
5.750 1.2753 0.01699 0.01074 -0.1543 0.6000 1.0000
6.000 1.2946 0.01726 0.01115 -0.1529 0.5922 1.0000
6.250 1.3235 0.01728 0.01116 -0.1531 0.5859 1.0000
6.500 1.3474 0.01746 0.01140 -0.1524 0.5788 1.0000
6.750 1.3723 0.01752 0.01152 -0.1519 0.5712 1.0000
7.000 1.3978 0.01762 0.01164 -0.1514 0.5638 1.0000
7.250 1.4203 0.01770 0.01179 -0.1504 0.5551 1.0000
7.500 1.4432 0.01780 0.01195 -0.1495 0.5466 1.0000
7.750 1.4662 0.01783 0.01202 -0.1486 0.5372 1.0000
8.000 1.4841 0.01800 0.01228 -0.1468 0.5269 1.0000
8.250 1.5062 0.01806 0.01236 -0.1456 0.5168 1.0000
8.500 1.5223 0.01822 0.01259 -0.1435 0.5051 1.0000
8.750 1.5359 0.01845 0.01291 -0.1410 0.4924 1.0000
9.000 1.5490 0.01869 0.01321 -0.1384 0.4791 1.0000
9.250 1.5584 0.01898 0.01353 -0.1351 0.4649 1.0000
9.500 1.5652 0.01939 0.01396 -0.1315 0.4494 1.0000
9.750 1.5701 0.01993 0.01451 -0.1277 0.4324 1.0000
10.000 1.5731 0.02063 0.01519 -0.1239 0.4136 1.0000
10.250 1.5740 0.02154 0.01604 -0.1200 0.3933 1.0000
10.500 1.5729 0.02267 0.01715 -0.1161 0.3711 1.0000
10.750 1.5693 0.02409 0.01850 -0.1122 0.3480 1.0000
11.000 1.5646 0.02576 0.02009 -0.1085 0.3244 1.0000
11.250 1.5578 0.02774 0.02198 -0.1050 0.3008 1.0000
11.500 1.5509 0.02993 0.02409 -0.1019 0.2777 1.0000
11.750 1.5431 0.03239 0.02647 -0.0991 0.2554 1.0000
12.000 1.5350 0.03505 0.02905 -0.0965 0.2346 1.0000
12.250 1.5279 0.03782 0.03176 -0.0944 0.2137 1.0000
12.500 1.5202 0.04080 0.03467 -0.0924 0.1946 1.0000
12.750 1.5122 0.04398 0.03778 -0.0908 0.1769 1.0000
13.000 1.5060 0.04715 0.04092 -0.0894 0.1595 1.0000
13.250 1.5000 0.05045 0.04418 -0.0883 0.1430 1.0000
13.500 1.4940 0.05389 0.04757 -0.0874 0.1279 1.0000
13.750 1.4882 0.05744 0.05109 -0.0866 0.1142 1.0000
14.000 1.4824 0.06109 0.05472 -0.0861 0.1019 1.0000
14.250 1.4767 0.06488 0.05848 -0.0857 0.0910 1.0000
14.500 1.4701 0.06886 0.06243 -0.0854 0.0817 1.0000
14.750 1.4650 0.07280 0.06636 -0.0854 0.0731 1.0000
15.000 1.4618 0.07658 0.07019 -0.0854 0.0654 1.0000
15.250 1.4569 0.08065 0.07428 -0.0856 0.0593 1.0000
15.500 1.4519 0.08482 0.07845 -0.0859 0.0542 1.0000
15.750 1.4505 0.08856 0.08228 -0.0862 0.0492 1.0000
16.000 1.4448 0.09289 0.08657 -0.0868 0.0456 1.0000
16.250 1.4454 0.09651 0.09033 -0.0873 0.0417 1.0000
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