USA 98 AIRFOIL (usa98-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 98 AIRFOIL (usa98-il) Reynolds number: 500,000 Max Cl/Cd: 112.65 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa98-il-500000-n5.txt Download as CSV file: xf-usa98-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 98 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1972 0.02953 0.02497 -0.1679 0.7925 0.0422
-8.250 -0.1718 0.02692 0.02209 -0.1719 0.7845 0.0424
-8.000 -0.1457 0.02503 0.01993 -0.1744 0.7770 0.0427
-7.750 -0.1187 0.02365 0.01836 -0.1761 0.7709 0.0431
-7.500 -0.0912 0.02245 0.01698 -0.1775 0.7645 0.0435
-7.250 -0.0634 0.02125 0.01557 -0.1788 0.7583 0.0439
-7.000 -0.0354 0.02005 0.01412 -0.1800 0.7527 0.0443
-6.750 -0.0068 0.01898 0.01287 -0.1810 0.7475 0.0446
-6.500 0.0218 0.01810 0.01181 -0.1818 0.7417 0.0450
-6.250 0.0506 0.01737 0.01090 -0.1824 0.7361 0.0453
-6.000 0.0795 0.01675 0.01012 -0.1830 0.7313 0.0456
-5.750 0.1087 0.01620 0.00946 -0.1835 0.7262 0.0458
-5.500 0.1378 0.01574 0.00888 -0.1839 0.7207 0.0460
-5.250 0.1666 0.01516 0.00822 -0.1843 0.7153 0.0464
-5.000 0.1956 0.01477 0.00778 -0.1847 0.7107 0.0467
-4.750 0.2249 0.01443 0.00742 -0.1850 0.7055 0.0470
-4.500 0.2540 0.01414 0.00709 -0.1853 0.7000 0.0473
-4.250 0.2829 0.01389 0.00678 -0.1855 0.6946 0.0477
-4.000 0.3122 0.01365 0.00650 -0.1858 0.6899 0.0482
-3.750 0.3415 0.01342 0.00624 -0.1860 0.6845 0.0487
-3.500 0.3706 0.01320 0.00596 -0.1862 0.6788 0.0493
-3.250 0.3995 0.01300 0.00569 -0.1864 0.6734 0.0498
-3.000 0.4290 0.01276 0.00543 -0.1866 0.6682 0.0503
-2.750 0.4582 0.01256 0.00519 -0.1868 0.6625 0.0507
-2.500 0.4871 0.01241 0.00497 -0.1869 0.6567 0.0511
-2.250 0.5162 0.01226 0.00479 -0.1871 0.6512 0.0514
-2.000 0.5456 0.01200 0.00453 -0.1874 0.6453 0.0521
-1.750 0.5745 0.01185 0.00437 -0.1875 0.6393 0.0527
-1.500 0.6034 0.01175 0.00425 -0.1876 0.6336 0.0533
-1.250 0.6325 0.01164 0.00414 -0.1878 0.6273 0.0540
-1.000 0.6613 0.01157 0.00404 -0.1879 0.6209 0.0549
-0.750 0.6898 0.01152 0.00396 -0.1879 0.6152 0.0559
-0.500 0.7188 0.01145 0.00389 -0.1880 0.6088 0.0568
-0.250 0.7473 0.01142 0.00382 -0.1880 0.6020 0.0575
0.000 0.7759 0.01134 0.00373 -0.1880 0.5960 0.0586
0.250 0.8047 0.01129 0.00369 -0.1881 0.5899 0.0597
0.500 0.8330 0.01128 0.00366 -0.1881 0.5831 0.0610
0.750 0.8610 0.01129 0.00365 -0.1880 0.5770 0.0624
1.000 0.8895 0.01129 0.00365 -0.1880 0.5708 0.0639
1.250 0.9175 0.01130 0.00365 -0.1879 0.5644 0.0662
1.500 0.9453 0.01134 0.00368 -0.1878 0.5583 0.0692
1.750 0.9734 0.01136 0.00371 -0.1877 0.5517 0.0726
2.000 1.0006 0.01141 0.00375 -0.1874 0.5440 0.0790
2.250 1.0280 0.01144 0.00381 -0.1872 0.5354 0.0944
2.500 1.0555 0.01120 0.00394 -0.1874 0.5250 0.2589
2.750 1.0825 0.01125 0.00408 -0.1872 0.5162 0.3091
3.000 1.1092 0.01133 0.00422 -0.1869 0.5084 0.3391
3.250 1.1357 0.01145 0.00436 -0.1865 0.5019 0.3634
3.500 1.1628 0.01153 0.00450 -0.1863 0.4954 0.3861
3.750 1.1892 0.01165 0.00466 -0.1859 0.4891 0.4078
4.000 1.2152 0.01179 0.00482 -0.1854 0.4830 0.4286
4.250 1.2417 0.01190 0.00498 -0.1850 0.4759 0.4500
4.500 1.2669 0.01205 0.00516 -0.1845 0.4686 0.4708
4.750 1.2928 0.01218 0.00533 -0.1840 0.4622 0.4903
5.000 1.3180 0.01233 0.00551 -0.1834 0.4539 0.5082
5.250 1.3422 0.01251 0.00571 -0.1826 0.4452 0.5264
5.500 1.3663 0.01268 0.00593 -0.1818 0.4345 0.5519
5.750 1.3898 0.01284 0.00619 -0.1809 0.4240 0.6060
6.000 1.4059 0.01248 0.00640 -0.1784 0.4141 1.0000
6.250 1.4290 0.01274 0.00664 -0.1774 0.4045 1.0000
6.500 1.4498 0.01308 0.00691 -0.1759 0.3934 1.0000
6.750 1.4709 0.01339 0.00718 -0.1746 0.3804 1.0000
7.000 1.4904 0.01377 0.00750 -0.1729 0.3668 1.0000
7.250 1.5070 0.01419 0.00785 -0.1707 0.3525 1.0000
7.500 1.5226 0.01467 0.00826 -0.1684 0.3375 1.0000
7.750 1.5376 0.01520 0.00872 -0.1659 0.3218 1.0000
8.250 1.5663 0.01640 0.00977 -0.1610 0.2900 1.0000
8.500 1.5790 0.01710 0.01039 -0.1584 0.2735 1.0000
8.750 1.5911 0.01784 0.01106 -0.1557 0.2578 1.0000
9.000 1.6042 0.01855 0.01173 -0.1533 0.2453 1.0000
9.250 1.6162 0.01934 0.01246 -0.1508 0.2339 1.0000
9.500 1.6266 0.02023 0.01330 -0.1480 0.2216 1.0000
9.750 1.6381 0.02109 0.01413 -0.1456 0.2099 1.0000
10.000 1.6491 0.02200 0.01501 -0.1431 0.1999 1.0000
10.250 1.6584 0.02306 0.01603 -0.1406 0.1896 1.0000
10.500 1.6693 0.02405 0.01701 -0.1383 0.1793 1.0000
10.750 1.6778 0.02523 0.01817 -0.1359 0.1686 1.0000
11.000 1.6844 0.02661 0.01950 -0.1334 0.1560 1.0000
11.250 1.6884 0.02825 0.02108 -0.1308 0.1404 1.0000
11.500 1.6879 0.03033 0.02307 -0.1280 0.1215 1.0000
11.750 1.6849 0.03276 0.02540 -0.1253 0.1020 1.0000
12.000 1.6823 0.03526 0.02784 -0.1228 0.0878 1.0000
12.250 1.6834 0.03752 0.03008 -0.1208 0.0794 1.0000
12.500 1.6868 0.03963 0.03221 -0.1191 0.0740 1.0000
12.750 1.6896 0.04186 0.03446 -0.1175 0.0699 1.0000
13.000 1.6945 0.04393 0.03657 -0.1160 0.0669 1.0000
13.250 1.6976 0.04618 0.03885 -0.1146 0.0641 1.0000
13.500 1.7007 0.04848 0.04120 -0.1133 0.0620 1.0000
13.750 1.7051 0.05070 0.04348 -0.1121 0.0601 1.0000
14.000 1.7081 0.05308 0.04592 -0.1109 0.0583 1.0000
14.250 1.7094 0.05571 0.04859 -0.1098 0.0566 1.0000
14.500 1.7111 0.05831 0.05125 -0.1088 0.0551 1.0000
14.750 1.7147 0.06074 0.05376 -0.1079 0.0538 1.0000
15.000 1.7166 0.06343 0.05651 -0.1070 0.0524 1.0000
15.250 1.7173 0.06628 0.05943 -0.1063 0.0511 1.0000
15.500 1.7170 0.06930 0.06250 -0.1055 0.0498 1.0000
15.750 1.7173 0.07229 0.06556 -0.1049 0.0487 1.0000
16.000 1.7191 0.07510 0.06845 -0.1044 0.0475 1.0000
16.250 1.7197 0.07811 0.07154 -0.1039 0.0463 1.0000
16.500 1.7187 0.08136 0.07486 -0.1036 0.0452 1.0000
16.750 1.7170 0.08472 0.07827 -0.1033 0.0441 1.0000
17.000 1.7151 0.08813 0.08175 -0.1030 0.0432 1.0000
17.250 1.7151 0.09131 0.08502 -0.1029 0.0422 1.0000
17.500 1.7144 0.09458 0.08837 -0.1028 0.0411 1.0000
17.750 1.7122 0.09812 0.09199 -0.1029 0.0400 1.0000
18.000 1.7098 0.10169 0.09562 -0.1030 0.0390 1.0000
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