EPPLER 399 AIRFOIL (e399-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 399 AIRFOIL (e399-il) Reynolds number: 200,000 Max Cl/Cd: 85.58 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e399-il-200000-n5.txt Download as CSV file: xf-e399-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.4411 0.09849 0.09473 -0.0649 1.0000 0.0120
-13.000 -0.4753 0.08926 0.08542 -0.0683 1.0000 0.0118
-12.750 -0.4962 0.08135 0.07741 -0.0729 0.9987 0.0116
-12.500 -0.5099 0.07225 0.06814 -0.0812 0.9943 0.0117
-12.250 -0.5183 0.06471 0.06046 -0.0886 0.9881 0.0118
-12.000 -0.5235 0.05783 0.05341 -0.0960 0.9810 0.0117
-11.500 -0.5292 0.04608 0.04133 -0.1090 0.9578 0.0123
-11.250 -0.5273 0.04097 0.03601 -0.1153 0.9449 0.0126
-11.000 -0.5194 0.03630 0.03115 -0.1222 0.9326 0.0130
-10.750 -0.5046 0.03228 0.02694 -0.1296 0.9205 0.0135
-10.500 -0.4807 0.02918 0.02359 -0.1364 0.9111 0.0147
-10.250 -0.4593 0.02705 0.02123 -0.1397 0.9005 0.0159
-10.000 -0.4357 0.02536 0.01938 -0.1423 0.8908 0.0172
-9.750 -0.4098 0.02384 0.01763 -0.1445 0.8819 0.0188
-9.500 -0.3870 0.02260 0.01626 -0.1457 0.8719 0.0206
-9.250 -0.3599 0.02150 0.01500 -0.1472 0.8640 0.0236
-9.000 -0.3370 0.02061 0.01397 -0.1475 0.8544 0.0268
-8.750 -0.3099 0.01977 0.01297 -0.1485 0.8467 0.0310
-8.500 -0.2860 0.01907 0.01217 -0.1487 0.8375 0.0355
-8.250 -0.2588 0.01842 0.01140 -0.1494 0.8303 0.0411
-8.000 -0.2342 0.01783 0.01074 -0.1495 0.8220 0.0470
-7.750 -0.2071 0.01728 0.01009 -0.1500 0.8151 0.0536
-7.500 -0.1815 0.01677 0.00952 -0.1502 0.8074 0.0605
-7.250 -0.1545 0.01631 0.00895 -0.1505 0.8003 0.0682
-7.000 -0.1276 0.01589 0.00845 -0.1508 0.7935 0.0767
-6.750 -0.1007 0.01552 0.00800 -0.1509 0.7866 0.0862
-6.500 -0.0726 0.01515 0.00755 -0.1514 0.7809 0.0969
-6.250 -0.0461 0.01480 0.00719 -0.1515 0.7740 0.1082
-6.000 -0.0184 0.01450 0.00682 -0.1518 0.7677 0.1204
-5.750 0.0096 0.01422 0.00649 -0.1520 0.7620 0.1337
-5.500 0.0369 0.01398 0.00621 -0.1522 0.7556 0.1480
-5.250 0.0652 0.01375 0.00594 -0.1525 0.7503 0.1634
-5.000 0.0933 0.01356 0.00570 -0.1528 0.7450 0.1794
-4.750 0.1209 0.01338 0.00551 -0.1529 0.7389 0.1958
-4.500 0.1493 0.01322 0.00531 -0.1532 0.7336 0.2131
-4.250 0.1777 0.01310 0.00515 -0.1534 0.7287 0.2307
-4.000 0.2055 0.01299 0.00503 -0.1536 0.7232 0.2479
-3.750 0.2339 0.01290 0.00491 -0.1538 0.7182 0.2652
-3.500 0.2627 0.01283 0.00478 -0.1540 0.7138 0.2819
-3.250 0.2904 0.01276 0.00472 -0.1541 0.7083 0.2979
-3.000 0.3186 0.01271 0.00465 -0.1543 0.7035 0.3136
-2.750 0.3473 0.01268 0.00457 -0.1545 0.6993 0.3287
-2.500 0.3754 0.01265 0.00453 -0.1546 0.6946 0.3435
-2.250 0.4032 0.01263 0.00450 -0.1547 0.6896 0.3582
-2.000 0.4316 0.01262 0.00446 -0.1548 0.6853 0.3729
-1.500 0.4880 0.01262 0.00445 -0.1551 0.6767 0.4024
-1.250 0.5158 0.01262 0.00447 -0.1551 0.6720 0.4171
-1.000 0.5442 0.01264 0.00448 -0.1553 0.6680 0.4320
-0.750 0.5729 0.01267 0.00449 -0.1555 0.6644 0.4471
-0.500 0.6000 0.01269 0.00456 -0.1555 0.6597 0.4625
-0.250 0.6277 0.01272 0.00462 -0.1555 0.6552 0.4783
0.000 0.6559 0.01276 0.00466 -0.1556 0.6514 0.4949
0.250 0.6844 0.01281 0.00471 -0.1557 0.6479 0.5117
0.500 0.7112 0.01285 0.00484 -0.1556 0.6432 0.5290
0.750 0.7385 0.01290 0.00495 -0.1556 0.6389 0.5470
1.000 0.7663 0.01295 0.00503 -0.1556 0.6351 0.5656
1.250 0.7944 0.01302 0.00512 -0.1557 0.6316 0.5849
1.500 0.8206 0.01309 0.00529 -0.1554 0.6270 0.6047
1.750 0.8472 0.01315 0.00543 -0.1552 0.6226 0.6252
2.000 0.8744 0.01322 0.00555 -0.1551 0.6187 0.6467
2.250 0.9017 0.01330 0.00566 -0.1550 0.6152 0.6682
2.500 0.9267 0.01339 0.00588 -0.1545 0.6104 0.6910
2.750 0.9524 0.01347 0.00605 -0.1541 0.6059 0.7150
3.000 0.9782 0.01353 0.00618 -0.1536 0.6020 0.7398
3.500 1.0262 0.01370 0.00656 -0.1521 0.5930 0.7956
3.750 1.0488 0.01375 0.00671 -0.1509 0.5883 0.8288
4.000 1.0706 0.01377 0.00680 -0.1495 0.5844 0.8694
4.250 1.0909 0.01374 0.00690 -0.1478 0.5794 0.9547
4.500 1.1178 0.01389 0.00709 -0.1478 0.5740 1.0000
4.750 1.1453 0.01406 0.00724 -0.1479 0.5691 1.0000
5.000 1.1714 0.01426 0.00747 -0.1478 0.5636 1.0000
5.250 1.1963 0.01445 0.00771 -0.1474 0.5573 1.0000
5.500 1.2230 0.01462 0.00786 -0.1473 0.5517 1.0000
5.750 1.2463 0.01483 0.00815 -0.1466 0.5444 1.0000
6.000 1.2708 0.01502 0.00836 -0.1461 0.5374 1.0000
6.250 1.2941 0.01523 0.00863 -0.1454 0.5299 1.0000
6.500 1.3171 0.01544 0.00887 -0.1447 0.5219 1.0000
6.750 1.3391 0.01567 0.00915 -0.1437 0.5135 1.0000
7.000 1.3607 0.01590 0.00941 -0.1427 0.5045 1.0000
7.250 1.3804 0.01617 0.00974 -0.1414 0.4944 1.0000
7.500 1.3997 0.01644 0.01004 -0.1399 0.4840 1.0000
7.750 1.4171 0.01675 0.01038 -0.1382 0.4722 1.0000
8.000 1.4314 0.01709 0.01075 -0.1359 0.4592 1.0000
8.250 1.4444 0.01749 0.01117 -0.1334 0.4454 1.0000
8.500 1.4561 0.01796 0.01164 -0.1307 0.4302 1.0000
8.750 1.4659 0.01853 0.01220 -0.1279 0.4133 1.0000
9.000 1.4736 0.01922 0.01286 -0.1248 0.3951 1.0000
9.250 1.4791 0.02006 0.01365 -0.1216 0.3758 1.0000
9.500 1.4834 0.02104 0.01458 -0.1184 0.3547 1.0000
9.750 1.4844 0.02225 0.01573 -0.1150 0.3326 1.0000
10.000 1.4840 0.02367 0.01708 -0.1117 0.3105 1.0000
10.250 1.4824 0.02530 0.01863 -0.1085 0.2877 1.0000
10.500 1.4792 0.02716 0.02041 -0.1054 0.2661 1.0000
10.750 1.4769 0.02913 0.02231 -0.1028 0.2444 1.0000
11.000 1.4735 0.03131 0.02443 -0.1003 0.2241 1.0000
11.250 1.4701 0.03363 0.02668 -0.0981 0.2051 1.0000
11.500 1.4679 0.03599 0.02899 -0.0961 0.1865 1.0000
11.750 1.4659 0.03844 0.03141 -0.0944 0.1696 1.0000
12.000 1.4643 0.04096 0.03390 -0.0929 0.1539 1.0000
12.250 1.4630 0.04356 0.03648 -0.0916 0.1394 1.0000
12.500 1.4624 0.04620 0.03910 -0.0905 0.1262 1.0000
12.750 1.4619 0.04891 0.04180 -0.0895 0.1140 1.0000
13.000 1.4616 0.05169 0.04458 -0.0886 0.1029 1.0000
13.250 1.4612 0.05458 0.04747 -0.0879 0.0926 1.0000
13.750 1.4615 0.06044 0.05337 -0.0869 0.0745 1.0000
14.000 1.4621 0.06345 0.05641 -0.0865 0.0669 1.0000
14.250 1.4619 0.06661 0.05960 -0.0863 0.0601 1.0000
14.500 1.4611 0.06992 0.06294 -0.0862 0.0539 1.0000
14.750 1.4621 0.07308 0.06616 -0.0861 0.0483 1.0000
15.000 1.4617 0.07648 0.06961 -0.0862 0.0436 1.0000
15.250 1.4607 0.08003 0.07322 -0.0864 0.0395 1.0000
15.500 1.4611 0.08346 0.07673 -0.0867 0.0359 1.0000
15.750 1.4591 0.08727 0.08059 -0.0872 0.0329 1.0000
16.000 1.4593 0.09084 0.08427 -0.0877 0.0300 1.0000
16.250 1.4567 0.09488 0.08837 -0.0884 0.0279 1.0000
16.500 1.4568 0.09856 0.09218 -0.0891 0.0256 1.0000
16.750 1.4539 0.10274 0.09642 -0.0901 0.0238 1.0000
17.000 1.4529 0.10668 0.10048 -0.0911 0.0220 1.0000
17.250 1.4509 0.11083 0.10473 -0.0922 0.0204 1.0000
17.500 1.4479 0.11517 0.10917 -0.0936 0.0192 1.0000
17.750 1.4464 0.11933 0.11345 -0.0950 0.0179 1.0000
18.000 1.4434 0.12374 0.11796 -0.0966 0.0168 1.0000
18.250 1.4401 0.12826 0.12258 -0.0984 0.0160 1.0000
18.500 1.4380 0.13260 0.12705 -0.1002 0.0150 1.0000
18.750 1.4348 0.13716 0.13172 -0.1022 0.0143 1.0000
19.000 1.4307 0.14193 0.13659 -0.1045 0.0137 1.0000
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