USA 98 AIRFOIL (usa98-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 98 AIRFOIL (usa98-il) Reynolds number: 200,000 Max Cl/Cd: 84.26 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa98-il-200000-n5.txt Download as CSV file: xf-usa98-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.0992 0.10390 0.09967 -0.0796 0.9498 0.0629
-8.750 -0.1106 0.09906 0.09481 -0.0866 0.9326 0.0642
-8.250 -0.0853 0.09111 0.08683 -0.0936 0.9041 0.0644
-8.000 -0.0577 0.08812 0.08380 -0.0957 0.8938 0.0648
-7.000 0.0056 0.06983 0.06510 -0.1152 0.8376 0.0571
-6.750 0.0216 0.06730 0.06249 -0.1174 0.8261 0.0567
-6.500 0.0353 0.06419 0.05928 -0.1206 0.8158 0.0562
-6.250 0.0478 0.06043 0.05546 -0.1249 0.8064 0.0558
-6.000 0.0621 0.05562 0.05055 -0.1314 0.7977 0.0554
-5.750 0.0930 0.03222 0.02609 -0.1698 0.7903 0.0553
-5.500 0.1229 0.02857 0.02195 -0.1746 0.7832 0.0556
-5.250 0.1533 0.02621 0.01915 -0.1774 0.7768 0.0560
-5.000 0.1835 0.02445 0.01701 -0.1794 0.7708 0.0565
-4.750 0.2129 0.02307 0.01532 -0.1807 0.7643 0.0569
-4.500 0.2430 0.02202 0.01393 -0.1818 0.7582 0.0576
-4.250 0.2721 0.02126 0.01307 -0.1825 0.7529 0.0582
-4.000 0.3002 0.02066 0.01242 -0.1828 0.7465 0.0588
-3.750 0.3291 0.02008 0.01175 -0.1833 0.7403 0.0594
-3.500 0.3584 0.01952 0.01104 -0.1837 0.7350 0.0599
-3.250 0.3875 0.01898 0.01040 -0.1841 0.7293 0.0605
-3.000 0.4162 0.01848 0.00981 -0.1843 0.7230 0.0611
-2.750 0.4453 0.01803 0.00925 -0.1846 0.7172 0.0618
-2.500 0.4747 0.01764 0.00874 -0.1848 0.7122 0.0625
-2.250 0.5031 0.01727 0.00832 -0.1849 0.7059 0.0633
-2.000 0.5319 0.01700 0.00796 -0.1850 0.6998 0.0642
-1.750 0.5607 0.01664 0.00760 -0.1852 0.6944 0.0654
-1.500 0.5891 0.01639 0.00738 -0.1853 0.6886 0.0665
-1.250 0.6175 0.01616 0.00716 -0.1854 0.6823 0.0677
-1.000 0.6463 0.01596 0.00692 -0.1854 0.6765 0.0687
-0.750 0.6750 0.01578 0.00672 -0.1855 0.6709 0.0699
-0.500 0.7033 0.01562 0.00657 -0.1855 0.6645 0.0712
-0.250 0.7319 0.01548 0.00641 -0.1856 0.6585 0.0724
0.000 0.7607 0.01534 0.00628 -0.1857 0.6530 0.0745
0.250 0.7888 0.01526 0.00625 -0.1857 0.6463 0.0771
0.500 0.8172 0.01521 0.00617 -0.1857 0.6402 0.0798
0.750 0.8459 0.01516 0.00606 -0.1857 0.6348 0.0825
1.000 0.8737 0.01510 0.00606 -0.1856 0.6279 0.0861
1.750 0.9588 0.01468 0.00607 -0.1860 0.6095 0.2231
2.000 0.9863 0.01463 0.00625 -0.1859 0.6030 0.3233
2.250 1.0138 0.01471 0.00637 -0.1857 0.5976 0.3616
2.500 1.0405 0.01479 0.00655 -0.1853 0.5908 0.3925
2.750 1.0671 0.01489 0.00670 -0.1849 0.5842 0.4192
3.000 1.0940 0.01501 0.00682 -0.1846 0.5784 0.4463
3.250 1.1197 0.01510 0.00702 -0.1841 0.5702 0.4752
3.500 1.1452 0.01520 0.00712 -0.1834 0.5612 0.5023
3.750 1.1700 0.01529 0.00728 -0.1827 0.5515 0.5246
4.000 1.1952 0.01540 0.00740 -0.1820 0.5432 0.5450
4.250 1.2205 0.01551 0.00760 -0.1814 0.5363 0.5723
4.500 1.2452 0.01557 0.00780 -0.1807 0.5292 0.6230
4.750 1.2632 0.01517 0.00785 -0.1782 0.5229 0.9692
5.000 1.2886 0.01539 0.00807 -0.1777 0.5156 1.0000
5.250 1.3133 0.01564 0.00828 -0.1770 0.5086 1.0000
5.500 1.3378 0.01591 0.00849 -0.1762 0.5020 1.0000
5.750 1.3616 0.01616 0.00875 -0.1754 0.4943 1.0000
6.000 1.3849 0.01645 0.00899 -0.1744 0.4868 1.0000
6.250 1.4081 0.01672 0.00928 -0.1734 0.4794 1.0000
6.500 1.4303 0.01702 0.00957 -0.1723 0.4712 1.0000
6.750 1.4515 0.01734 0.00987 -0.1710 0.4624 1.0000
7.000 1.4712 0.01767 0.01019 -0.1693 0.4517 1.0000
7.250 1.4902 0.01803 0.01053 -0.1676 0.4411 1.0000
7.500 1.5072 0.01843 0.01089 -0.1655 0.4301 1.0000
7.750 1.5245 0.01881 0.01129 -0.1635 0.4188 1.0000
8.000 1.5385 0.01926 0.01172 -0.1608 0.4080 1.0000
8.250 1.5517 0.01976 0.01221 -0.1581 0.3960 1.0000
8.500 1.5649 0.02031 0.01274 -0.1555 0.3832 1.0000
8.750 1.5764 0.02094 0.01336 -0.1526 0.3698 1.0000
9.000 1.5868 0.02166 0.01404 -0.1497 0.3568 1.0000
9.250 1.5973 0.02242 0.01478 -0.1468 0.3429 1.0000
9.500 1.6062 0.02329 0.01562 -0.1439 0.3281 1.0000
9.750 1.6139 0.02427 0.01656 -0.1408 0.3137 1.0000
10.000 1.6205 0.02537 0.01763 -0.1378 0.2998 1.0000
10.250 1.6256 0.02661 0.01882 -0.1348 0.2860 1.0000
10.750 1.6349 0.02940 0.02156 -0.1291 0.2596 1.0000
11.000 1.6397 0.03091 0.02307 -0.1266 0.2484 1.0000
11.250 1.6426 0.03264 0.02477 -0.1240 0.2383 1.0000
11.500 1.6488 0.03422 0.02639 -0.1220 0.2280 1.0000
11.750 1.6522 0.03608 0.02825 -0.1199 0.2187 1.0000
12.000 1.6555 0.03802 0.03020 -0.1179 0.2087 1.0000
12.250 1.6593 0.03997 0.03219 -0.1161 0.1989 1.0000
12.500 1.6600 0.04227 0.03449 -0.1143 0.1889 1.0000
12.750 1.6622 0.04450 0.03674 -0.1126 0.1772 1.0000
13.000 1.6624 0.04697 0.03922 -0.1110 0.1648 1.0000
13.250 1.6602 0.04976 0.04198 -0.1094 0.1508 1.0000
13.500 1.6553 0.05290 0.04509 -0.1079 0.1355 1.0000
14.000 1.6403 0.05999 0.05209 -0.1051 0.1070 1.0000
14.250 1.6329 0.06367 0.05575 -0.1040 0.0971 1.0000
14.500 1.6272 0.06726 0.05934 -0.1031 0.0900 1.0000
14.750 1.6225 0.07079 0.06292 -0.1023 0.0850 1.0000
15.000 1.6179 0.07440 0.06657 -0.1016 0.0809 1.0000
15.250 1.6133 0.07808 0.07031 -0.1012 0.0777 1.0000
15.500 1.6106 0.08157 0.07387 -0.1008 0.0747 1.0000
15.750 1.6058 0.08538 0.07775 -0.1005 0.0722 1.0000
16.000 1.5998 0.08940 0.08183 -0.1004 0.0702 1.0000
16.250 1.5987 0.09278 0.08532 -0.1003 0.0681 1.0000
16.500 1.5957 0.09648 0.08910 -0.1004 0.0661 1.0000
16.750 1.5913 0.10038 0.09307 -0.1006 0.0644 1.0000
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Polar data table (+)
Polar graphs
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