EPPLER 399 AIRFOIL (e399-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 399 AIRFOIL (e399-il) Reynolds number: 500,000 Max Cl/Cd: 123.25 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e399-il-500000-n5.txt Download as CSV file: xf-e399-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.4657 0.13054 0.12783 -0.0537 1.0000 0.0055
-15.750 -0.4815 0.12332 0.12054 -0.0565 1.0000 0.0055
-15.500 -0.4964 0.11659 0.11375 -0.0591 1.0000 0.0055
-15.250 -0.5108 0.11020 0.10730 -0.0617 1.0000 0.0055
-15.000 -0.5222 0.10469 0.10174 -0.0638 1.0000 0.0054
-14.750 -0.5354 0.09899 0.09600 -0.0660 1.0000 0.0053
-14.500 -0.5547 0.09242 0.08936 -0.0686 1.0000 0.0054
-14.250 -0.5670 0.08532 0.08218 -0.0735 0.9992 0.0054
-14.000 -0.5769 0.07769 0.07444 -0.0800 0.9974 0.0054
-13.750 -0.5888 0.07004 0.06668 -0.0868 0.9946 0.0054
-13.500 -0.6008 0.06295 0.05948 -0.0931 0.9907 0.0053
-13.250 -0.6126 0.05579 0.05218 -0.0999 0.9852 0.0054
-13.000 -0.6255 0.04921 0.04547 -0.1058 0.9755 0.0054
-12.500 -0.6348 0.03707 0.03302 -0.1195 0.9472 0.0054
-12.250 -0.6159 0.03165 0.02737 -0.1297 0.9358 0.0056
-12.000 -0.5867 0.02686 0.02233 -0.1412 0.9229 0.0057
-11.750 -0.5620 0.02379 0.01899 -0.1487 0.9040 0.0059
-11.500 -0.5426 0.02217 0.01716 -0.1512 0.8864 0.0061
-11.250 -0.5275 0.02078 0.01557 -0.1519 0.8705 0.0063
-11.000 -0.5098 0.01977 0.01441 -0.1520 0.8578 0.0066
-10.750 -0.4902 0.01894 0.01342 -0.1520 0.8465 0.0069
-10.500 -0.4700 0.01817 0.01252 -0.1519 0.8355 0.0074
-10.250 -0.4483 0.01750 0.01170 -0.1518 0.8258 0.0079
-10.000 -0.4264 0.01680 0.01088 -0.1517 0.8160 0.0086
-9.750 -0.4032 0.01620 0.01018 -0.1517 0.8074 0.0094
-9.500 -0.3793 0.01566 0.00952 -0.1516 0.7992 0.0105
-9.250 -0.3549 0.01511 0.00889 -0.1517 0.7915 0.0120
-9.000 -0.3300 0.01464 0.00832 -0.1517 0.7836 0.0137
-8.750 -0.3046 0.01418 0.00780 -0.1517 0.7762 0.0163
-8.500 -0.2789 0.01377 0.00732 -0.1518 0.7685 0.0194
-8.250 -0.2528 0.01338 0.00688 -0.1519 0.7621 0.0233
-8.000 -0.2262 0.01301 0.00646 -0.1521 0.7553 0.0277
-7.750 -0.1997 0.01268 0.00608 -0.1522 0.7488 0.0326
-7.500 -0.1726 0.01236 0.00573 -0.1524 0.7424 0.0383
-7.250 -0.1456 0.01206 0.00539 -0.1525 0.7357 0.0443
-7.000 -0.1183 0.01178 0.00508 -0.1527 0.7299 0.0516
-6.750 -0.0907 0.01150 0.00479 -0.1529 0.7241 0.0596
-6.500 -0.0630 0.01127 0.00452 -0.1531 0.7183 0.0674
-6.250 -0.0352 0.01106 0.00427 -0.1533 0.7130 0.0760
-6.000 -0.0072 0.01083 0.00404 -0.1535 0.7072 0.0860
-5.750 0.0207 0.01063 0.00382 -0.1537 0.7015 0.0970
-5.500 0.0488 0.01045 0.00362 -0.1540 0.6967 0.1082
-5.250 0.0772 0.01026 0.00344 -0.1542 0.6917 0.1200
-5.000 0.1055 0.01011 0.00327 -0.1544 0.6865 0.1320
-4.500 0.1622 0.00984 0.00299 -0.1549 0.6768 0.1595
-4.250 0.1907 0.00971 0.00286 -0.1552 0.6720 0.1744
-4.000 0.2191 0.00961 0.00275 -0.1554 0.6675 0.1893
-3.750 0.2476 0.00952 0.00266 -0.1556 0.6632 0.2047
-3.500 0.2763 0.00942 0.00258 -0.1559 0.6585 0.2207
-3.250 0.3048 0.00935 0.00251 -0.1561 0.6540 0.2366
-2.750 0.3619 0.00924 0.00241 -0.1565 0.6460 0.2673
-2.500 0.3906 0.00919 0.00238 -0.1568 0.6417 0.2820
-2.250 0.4191 0.00916 0.00235 -0.1569 0.6374 0.2958
-2.000 0.4474 0.00915 0.00232 -0.1571 0.6336 0.3089
-1.750 0.4760 0.00913 0.00231 -0.1573 0.6299 0.3217
-1.500 0.5046 0.00911 0.00231 -0.1575 0.6257 0.3350
-1.250 0.5331 0.00910 0.00231 -0.1577 0.6217 0.3482
-1.000 0.5614 0.00911 0.00232 -0.1578 0.6179 0.3605
-0.750 0.5897 0.00913 0.00234 -0.1580 0.6143 0.3734
-0.500 0.6183 0.00912 0.00236 -0.1582 0.6105 0.3869
-0.250 0.6466 0.00913 0.00239 -0.1583 0.6066 0.4004
0.000 0.6748 0.00915 0.00243 -0.1584 0.6027 0.4137
0.250 0.7028 0.00919 0.00247 -0.1585 0.5992 0.4273
0.500 0.7313 0.00920 0.00253 -0.1587 0.5956 0.4418
0.750 0.7594 0.00922 0.00259 -0.1588 0.5916 0.4566
1.000 0.7874 0.00925 0.00265 -0.1589 0.5876 0.4720
1.250 0.8152 0.00931 0.00272 -0.1590 0.5840 0.4875
1.500 0.8433 0.00933 0.00281 -0.1591 0.5804 0.5037
1.750 0.8712 0.00936 0.00290 -0.1592 0.5763 0.5205
2.000 0.8989 0.00941 0.00299 -0.1592 0.5722 0.5379
2.250 0.9262 0.00947 0.00309 -0.1592 0.5682 0.5558
2.500 0.9539 0.00952 0.00320 -0.1593 0.5644 0.5744
2.750 0.9815 0.00956 0.00331 -0.1593 0.5599 0.5929
3.000 1.0086 0.00963 0.00343 -0.1592 0.5554 0.6122
3.500 1.0625 0.00976 0.00370 -0.1590 0.5464 0.6519
3.750 1.0891 0.00982 0.00384 -0.1588 0.5412 0.6735
4.000 1.1151 0.00992 0.00398 -0.1585 0.5360 0.6955
4.250 1.1414 0.00998 0.00414 -0.1583 0.5305 0.7183
4.500 1.1669 0.01006 0.00430 -0.1579 0.5239 0.7429
4.750 1.1914 0.01016 0.00447 -0.1573 0.5175 0.7688
5.000 1.2160 0.01023 0.00464 -0.1567 0.5101 0.7977
5.250 1.2382 0.01034 0.00482 -0.1556 0.5028 0.8306
5.500 1.2592 0.01037 0.00499 -0.1542 0.4950 0.8716
5.750 1.2758 0.01037 0.00507 -0.1518 0.4869 1.0000
6.000 1.3003 0.01055 0.00527 -0.1513 0.4768 1.0000
6.250 1.3233 0.01078 0.00549 -0.1505 0.4663 1.0000
6.500 1.3447 0.01106 0.00573 -0.1495 0.4543 1.0000
6.750 1.3653 0.01135 0.00599 -0.1483 0.4405 1.0000
7.000 1.3840 0.01168 0.00628 -0.1467 0.4252 1.0000
7.250 1.4000 0.01205 0.00661 -0.1447 0.4089 1.0000
7.500 1.4143 0.01250 0.00700 -0.1423 0.3907 1.0000
7.750 1.4275 0.01301 0.00744 -0.1399 0.3703 1.0000
8.000 1.4379 0.01364 0.00798 -0.1370 0.3479 1.0000
8.250 1.4474 0.01434 0.00859 -0.1341 0.3259 1.0000
8.500 1.4547 0.01517 0.00930 -0.1310 0.3013 1.0000
8.750 1.4603 0.01611 0.01014 -0.1277 0.2769 1.0000
9.000 1.4641 0.01719 0.01111 -0.1244 0.2524 1.0000
9.250 1.4672 0.01839 0.01219 -0.1212 0.2276 1.0000
9.500 1.4692 0.01973 0.01342 -0.1180 0.2047 1.0000
9.750 1.4723 0.02109 0.01470 -0.1152 0.1838 1.0000
10.000 1.4762 0.02250 0.01604 -0.1126 0.1663 1.0000
10.250 1.4799 0.02400 0.01749 -0.1102 0.1501 1.0000
10.500 1.4834 0.02559 0.01903 -0.1080 0.1350 1.0000
10.750 1.4877 0.02721 0.02061 -0.1060 0.1217 1.0000
11.000 1.4912 0.02896 0.02232 -0.1041 0.1088 1.0000
11.250 1.4946 0.03078 0.02411 -0.1023 0.0968 1.0000
11.500 1.4984 0.03265 0.02597 -0.1007 0.0864 1.0000
11.750 1.5017 0.03463 0.02793 -0.0992 0.0766 1.0000
12.000 1.5048 0.03670 0.02999 -0.0978 0.0676 1.0000
12.250 1.5080 0.03882 0.03211 -0.0965 0.0598 1.0000
12.500 1.5111 0.04102 0.03431 -0.0953 0.0531 1.0000
12.750 1.5146 0.04325 0.03654 -0.0943 0.0466 1.0000
13.000 1.5178 0.04557 0.03888 -0.0934 0.0407 1.0000
13.250 1.5212 0.04794 0.04127 -0.0925 0.0358 1.0000
13.500 1.5243 0.05040 0.04376 -0.0918 0.0318 1.0000
13.750 1.5270 0.05296 0.04634 -0.0912 0.0278 1.0000
14.000 1.5311 0.05544 0.04886 -0.0907 0.0248 1.0000
14.250 1.5344 0.05805 0.05153 -0.0903 0.0225 1.0000
14.500 1.5378 0.06070 0.05423 -0.0899 0.0203 1.0000
14.750 1.5412 0.06342 0.05701 -0.0897 0.0184 1.0000
15.000 1.5434 0.06633 0.05997 -0.0895 0.0167 1.0000
15.250 1.5468 0.06914 0.06285 -0.0894 0.0152 1.0000
15.500 1.5482 0.07226 0.06603 -0.0894 0.0137 1.0000
15.750 1.5508 0.07529 0.06913 -0.0895 0.0126 1.0000
16.000 1.5525 0.07847 0.07238 -0.0897 0.0115 1.0000
16.250 1.5537 0.08178 0.07577 -0.0900 0.0105 1.0000
16.500 1.5555 0.08505 0.07913 -0.0904 0.0097 1.0000
16.750 1.5554 0.08864 0.08278 -0.0909 0.0089 1.0000
17.000 1.5564 0.09212 0.08635 -0.0914 0.0083 1.0000
17.250 1.5571 0.09568 0.09000 -0.0921 0.0075 1.0000
17.500 1.5560 0.09957 0.09397 -0.0929 0.0070 1.0000
17.750 1.5559 0.10334 0.09783 -0.0938 0.0065 1.0000
18.000 1.5556 0.10714 0.10173 -0.0948 0.0060 1.0000
18.250 1.5541 0.11121 0.10589 -0.0960 0.0056 1.0000
18.500 1.5518 0.11542 0.11018 -0.0973 0.0053 1.0000
18.750 1.5507 0.11945 0.11432 -0.0987 0.0050 1.0000
19.000 1.5490 0.12364 0.11861 -0.1002 0.0047 1.0000
19.250 1.5468 0.12792 0.12299 -0.1018 0.0044 1.0000
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