EPPLER 398 AIRFOIL (e398-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 398 AIRFOIL (e398-il) Reynolds number: 200,000 Max Cl/Cd: 84.76 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e398-il-200000.txt Download as CSV file: xf-e398-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 398 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3749 0.06883 0.06553 -0.0899 0.9785 0.0243
-10.250 -0.3975 0.05578 0.05226 -0.1061 0.9677 0.0238
-10.000 -0.4058 0.04676 0.04297 -0.1199 0.9544 0.0232
-9.750 -0.4042 0.03880 0.03443 -0.1339 0.9410 0.0233
-9.500 -0.3877 0.03396 0.02889 -0.1407 0.9324 0.0243
-9.250 -0.3583 0.03087 0.02559 -0.1450 0.9283 0.0257
-9.000 -0.3344 0.02922 0.02376 -0.1464 0.9195 0.0274
-8.750 -0.3017 0.02643 0.02044 -0.1498 0.9153 0.0292
-8.500 -0.2791 0.02457 0.01852 -0.1503 0.9066 0.0315
-8.250 -0.2462 0.02308 0.01669 -0.1523 0.9011 0.0354
-8.000 -0.2194 0.02191 0.01554 -0.1532 0.8937 0.0404
-7.750 -0.1908 0.02077 0.01432 -0.1542 0.8865 0.0470
-7.500 -0.1620 0.01984 0.01327 -0.1551 0.8797 0.0549
-7.250 -0.1356 0.01904 0.01237 -0.1554 0.8717 0.0634
-7.000 -0.1047 0.01832 0.01152 -0.1565 0.8661 0.0733
-6.750 -0.0797 0.01799 0.01106 -0.1562 0.8573 0.0825
-6.500 -0.0494 0.01728 0.01030 -0.1571 0.8517 0.0936
-6.250 -0.0253 0.01677 0.00979 -0.1567 0.8433 0.1043
-6.000 0.0040 0.01625 0.00920 -0.1572 0.8374 0.1175
-5.750 0.0306 0.01585 0.00877 -0.1573 0.8306 0.1315
-5.500 0.0583 0.01548 0.00836 -0.1574 0.8238 0.1473
-5.250 0.0884 0.01516 0.00796 -0.1580 0.8187 0.1655
-5.000 0.1138 0.01496 0.00773 -0.1577 0.8112 0.1835
-4.750 0.1430 0.01467 0.00744 -0.1582 0.8059 0.2032
-4.500 0.1706 0.01451 0.00728 -0.1583 0.8000 0.2230
-4.250 0.1979 0.01438 0.00713 -0.1583 0.7935 0.2436
-4.000 0.2280 0.01424 0.00692 -0.1587 0.7888 0.2652
-3.750 0.2545 0.01417 0.00689 -0.1587 0.7829 0.2851
-3.500 0.2823 0.01410 0.00681 -0.1587 0.7772 0.3059
-3.250 0.3125 0.01403 0.00665 -0.1592 0.7728 0.3277
-3.000 0.3389 0.01401 0.00667 -0.1590 0.7670 0.3474
-2.750 0.3665 0.01396 0.00665 -0.1590 0.7616 0.3673
-2.500 0.3963 0.01392 0.00656 -0.1594 0.7574 0.3884
-2.250 0.4234 0.01394 0.00660 -0.1593 0.7522 0.4090
-2.000 0.4504 0.01394 0.00662 -0.1592 0.7468 0.4294
-1.750 0.4795 0.01390 0.00660 -0.1595 0.7426 0.4503
-1.500 0.5082 0.01393 0.00662 -0.1596 0.7384 0.4719
-1.250 0.5340 0.01399 0.00672 -0.1594 0.7327 0.4941
-1.000 0.5621 0.01397 0.00676 -0.1594 0.7283 0.5160
-0.750 0.5922 0.01398 0.00675 -0.1598 0.7247 0.5406
-0.500 0.6172 0.01406 0.00695 -0.1593 0.7193 0.5641
-0.250 0.6440 0.01410 0.00705 -0.1591 0.7145 0.5898
0.000 0.6727 0.01411 0.00709 -0.1592 0.7107 0.6166
0.250 0.7002 0.01418 0.00722 -0.1591 0.7066 0.6450
0.500 0.7245 0.01428 0.00744 -0.1584 0.7012 0.6744
0.750 0.7509 0.01430 0.00755 -0.1580 0.6970 0.7049
1.000 0.7788 0.01432 0.00760 -0.1578 0.6935 0.7377
1.250 0.8008 0.01444 0.00786 -0.1566 0.6885 0.7716
1.500 0.8223 0.01449 0.00804 -0.1552 0.6836 0.8078
1.750 0.8440 0.01446 0.00808 -0.1535 0.6798 0.8501
2.000 0.8637 0.01438 0.00804 -0.1513 0.6764 0.9048
2.250 0.8900 0.01445 0.00821 -0.1513 0.6706 1.0000
2.500 0.9208 0.01462 0.00832 -0.1522 0.6660 1.0000
2.750 0.9534 0.01475 0.00835 -0.1533 0.6624 1.0000
3.000 0.9799 0.01503 0.00865 -0.1534 0.6574 1.0000
3.250 1.0068 0.01525 0.00888 -0.1534 0.6521 1.0000
3.500 1.0371 0.01538 0.00895 -0.1540 0.6480 1.0000
3.750 1.0663 0.01559 0.00914 -0.1544 0.6437 1.0000
4.000 1.0901 0.01586 0.00948 -0.1539 0.6376 1.0000
4.250 1.1194 0.01598 0.00957 -0.1542 0.6329 1.0000
4.500 1.1497 0.01613 0.00969 -0.1547 0.6286 1.0000
4.750 1.1718 0.01641 0.01008 -0.1539 0.6219 1.0000
5.000 1.2010 0.01649 0.01014 -0.1541 0.6168 1.0000
5.250 1.2284 0.01668 0.01034 -0.1541 0.6114 1.0000
5.500 1.2520 0.01686 0.01060 -0.1534 0.6044 1.0000
5.750 1.2835 0.01686 0.01055 -0.1540 0.5992 1.0000
6.000 1.3043 0.01712 0.01093 -0.1529 0.5916 1.0000
6.250 1.3325 0.01715 0.01097 -0.1529 0.5853 1.0000
6.500 1.3563 0.01733 0.01121 -0.1522 0.5780 1.0000
6.750 1.3818 0.01736 0.01128 -0.1517 0.5703 1.0000
7.000 1.4049 0.01749 0.01148 -0.1508 0.5621 1.0000
7.250 1.4303 0.01750 0.01151 -0.1503 0.5538 1.0000
7.500 1.4504 0.01767 0.01178 -0.1489 0.5446 1.0000
7.750 1.4773 0.01764 0.01173 -0.1486 0.5359 1.0000
8.000 1.4932 0.01783 0.01206 -0.1465 0.5248 1.0000
8.250 1.5119 0.01797 0.01228 -0.1448 0.5139 1.0000
8.500 1.5309 0.01810 0.01244 -0.1432 0.5023 1.0000
8.750 1.5478 0.01826 0.01263 -0.1411 0.4894 1.0000
9.000 1.5602 0.01853 0.01296 -0.1384 0.4750 1.0000
9.250 1.5693 0.01885 0.01331 -0.1351 0.4593 1.0000
9.500 1.5745 0.01930 0.01380 -0.1312 0.4426 1.0000
9.750 1.5781 0.01989 0.01441 -0.1273 0.4241 1.0000
10.000 1.5802 0.02064 0.01515 -0.1233 0.4038 1.0000
10.250 1.5803 0.02162 0.01607 -0.1193 0.3824 1.0000
10.500 1.5785 0.02284 0.01724 -0.1154 0.3586 1.0000
10.750 1.5739 0.02436 0.01867 -0.1115 0.3347 1.0000
11.000 1.5682 0.02614 0.02037 -0.1078 0.3102 1.0000
11.250 1.5617 0.02818 0.02233 -0.1044 0.2864 1.0000
11.500 1.5537 0.03052 0.02457 -0.1013 0.2635 1.0000
11.750 1.5464 0.03301 0.02700 -0.0986 0.2410 1.0000
12.000 1.5383 0.03575 0.02965 -0.0962 0.2199 1.0000
12.250 1.5305 0.03864 0.03247 -0.0941 0.2000 1.0000
12.500 1.5238 0.04160 0.03538 -0.0923 0.1805 1.0000
12.750 1.5163 0.04480 0.03852 -0.0907 0.1625 1.0000
13.000 1.5087 0.04816 0.04182 -0.0894 0.1460 1.0000
13.250 1.5023 0.05156 0.04517 -0.0883 0.1303 1.0000
13.500 1.4965 0.05503 0.04861 -0.0875 0.1157 1.0000
13.750 1.4903 0.05866 0.05221 -0.0868 0.1026 1.0000
14.000 1.4837 0.06247 0.05598 -0.0863 0.0911 1.0000
14.250 1.4777 0.06634 0.05983 -0.0859 0.0809 1.0000
14.500 1.4740 0.07003 0.06355 -0.0857 0.0717 1.0000
14.750 1.4695 0.07390 0.06746 -0.0856 0.0642 1.0000
15.000 1.4613 0.07835 0.07185 -0.0857 0.0584 1.0000
15.250 1.4615 0.08180 0.07542 -0.0859 0.0525 1.0000
15.500 1.4551 0.08614 0.07975 -0.0862 0.0482 1.0000
15.750 1.4549 0.08976 0.08350 -0.0866 0.0439 1.0000
16.000 1.4492 0.09408 0.08777 -0.0871 0.0405 1.0000
16.250 1.4500 0.09768 0.09153 -0.0876 0.0371 1.0000
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Polar data table (+)
Polar graphs
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