USA 98 AIRFOIL (usa98-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 98 AIRFOIL (usa98-il) Reynolds number: 200,000 Max Cl/Cd: 84.09 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa98-il-200000.txt Download as CSV file: xf-usa98-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.0968 0.10151 0.09759 -0.0769 0.9690 0.0766
-8.000 -0.0818 0.09814 0.09421 -0.0807 0.9598 0.0787
-7.750 -0.0894 0.09299 0.08905 -0.0922 0.9462 0.0813
-7.500 -0.0582 0.08961 0.08567 -0.0930 0.9441 0.0819
-7.250 -0.0286 0.08647 0.08252 -0.0954 0.9418 0.0829
-7.000 -0.0113 0.08389 0.07994 -0.0968 0.9313 0.0844
-6.750 -0.0152 0.07756 0.07356 -0.1157 0.9135 0.0903
-6.500 0.0070 0.07488 0.07088 -0.1128 0.9084 0.0908
-6.250 0.0306 0.07256 0.06855 -0.1123 0.9012 0.0916
-6.000 0.0595 0.06992 0.06587 -0.1145 0.8963 0.0930
-5.750 0.0801 0.06738 0.06330 -0.1172 0.8860 0.0951
-5.500 0.1058 0.06019 0.05598 -0.1350 0.8754 0.1016
-5.250 0.1497 0.05213 0.04749 -0.1586 0.8649 0.1123
-5.000 0.1679 0.05059 0.04608 -0.1547 0.8573 0.1130
-4.750 0.1863 0.04999 0.04551 -0.1514 0.8490 0.1138
-4.500 0.2081 0.04913 0.04461 -0.1498 0.8418 0.1151
-4.250 0.2406 0.04583 0.04117 -0.1575 0.8325 0.1236
-4.000 0.2872 0.03965 0.03441 -0.1731 0.8254 0.1402
-3.750 0.3043 0.03806 0.03299 -0.1711 0.8171 0.1415
-3.500 0.3267 0.03731 0.03228 -0.1698 0.8098 0.1432
-3.250 0.3931 0.02497 0.01816 -0.1874 0.8046 0.1022
-3.000 0.4216 0.02342 0.01645 -0.1879 0.7966 0.0969
-2.750 0.4572 0.02196 0.01425 -0.1893 0.7898 0.0904
-2.500 0.4875 0.02114 0.01324 -0.1899 0.7836 0.0899
-2.250 0.5156 0.02033 0.01232 -0.1900 0.7759 0.0898
-2.000 0.5459 0.01976 0.01156 -0.1904 0.7693 0.0901
-1.750 0.5753 0.01891 0.01064 -0.1908 0.7631 0.0915
-1.500 0.6027 0.01843 0.01016 -0.1907 0.7557 0.0929
-1.250 0.6323 0.01802 0.00968 -0.1909 0.7493 0.0940
-1.000 0.6618 0.01771 0.00931 -0.1910 0.7433 0.0952
-0.750 0.6889 0.01742 0.00903 -0.1907 0.7359 0.0966
-0.500 0.7183 0.01715 0.00872 -0.1908 0.7297 0.0983
-0.250 0.7482 0.01704 0.00853 -0.1909 0.7240 0.1005
0.000 0.7748 0.01666 0.00830 -0.1907 0.7165 0.1042
0.250 0.8040 0.01647 0.00813 -0.1908 0.7102 0.1081
0.500 0.8347 0.01640 0.00798 -0.1911 0.7050 0.1121
0.750 0.8613 0.01622 0.00793 -0.1909 0.6975 0.1182
1.000 0.8906 0.01607 0.00779 -0.1910 0.6910 0.1298
1.250 0.9227 0.01555 0.00779 -0.1920 0.6859 0.2946
1.500 0.9481 0.01566 0.00817 -0.1914 0.6786 0.4048
1.750 0.9758 0.01577 0.00831 -0.1911 0.6720 0.4420
2.000 1.0054 0.01587 0.00838 -0.1911 0.6668 0.4701
2.250 1.0305 0.01599 0.00860 -0.1905 0.6596 0.4926
2.500 1.0577 0.01603 0.00868 -0.1902 0.6530 0.5170
2.750 1.0870 0.01605 0.00870 -0.1902 0.6476 0.5464
3.000 1.1114 0.01610 0.00893 -0.1894 0.6402 0.5806
3.250 1.1380 0.01599 0.00894 -0.1889 0.6326 0.6208
3.500 1.1641 0.01584 0.00894 -0.1882 0.6251 0.6823
3.750 1.1832 0.01533 0.00884 -0.1859 0.6165 1.0000
4.000 1.2129 0.01546 0.00880 -0.1861 0.6101 1.0000
4.250 1.2381 0.01568 0.00901 -0.1855 0.6026 1.0000
4.500 1.2649 0.01585 0.00912 -0.1851 0.5955 1.0000
4.750 1.2937 0.01604 0.00919 -0.1851 0.5894 1.0000
5.000 1.3171 0.01627 0.00946 -0.1842 0.5814 1.0000
5.250 1.3442 0.01644 0.00958 -0.1838 0.5747 1.0000
5.500 1.3700 0.01669 0.00980 -0.1833 0.5676 1.0000
5.750 1.3941 0.01690 0.01002 -0.1825 0.5596 1.0000
6.000 1.4225 0.01712 0.01013 -0.1824 0.5530 1.0000
6.250 1.4438 0.01739 0.01049 -0.1811 0.5446 1.0000
6.500 1.4692 0.01758 0.01061 -0.1804 0.5364 1.0000
6.750 1.4906 0.01782 0.01089 -0.1790 0.5268 1.0000
7.000 1.5145 0.01801 0.01101 -0.1781 0.5172 1.0000
7.250 1.5341 0.01828 0.01134 -0.1764 0.5070 1.0000
7.500 1.5577 0.01853 0.01150 -0.1754 0.4978 1.0000
7.750 1.5748 0.01882 0.01189 -0.1732 0.4869 1.0000
8.000 1.5956 0.01911 0.01212 -0.1718 0.4767 1.0000
8.250 1.6118 0.01942 0.01248 -0.1694 0.4652 1.0000
8.500 1.6282 0.01977 0.01285 -0.1672 0.4538 1.0000
8.750 1.6445 0.02015 0.01316 -0.1649 0.4425 1.0000
9.000 1.6555 0.02056 0.01365 -0.1617 0.4297 1.0000
9.250 1.6647 0.02102 0.01412 -0.1582 0.4168 1.0000
9.500 1.6731 0.02159 0.01464 -0.1546 0.4041 1.0000
9.750 1.6804 0.02223 0.01529 -0.1509 0.3904 1.0000
10.000 1.6867 0.02297 0.01604 -0.1473 0.3756 1.0000
10.250 1.6929 0.02382 0.01687 -0.1437 0.3610 1.0000
10.500 1.6986 0.02477 0.01781 -0.1403 0.3471 1.0000
10.750 1.7033 0.02585 0.01885 -0.1369 0.3336 1.0000
11.000 1.7069 0.02706 0.02004 -0.1335 0.3200 1.0000
11.250 1.7112 0.02833 0.02133 -0.1304 0.3063 1.0000
11.500 1.7146 0.02975 0.02274 -0.1274 0.2935 1.0000
11.750 1.7163 0.03136 0.02434 -0.1245 0.2813 1.0000
12.000 1.7167 0.03318 0.02612 -0.1216 0.2689 1.0000
12.250 1.7185 0.03502 0.02801 -0.1192 0.2561 1.0000
12.500 1.7184 0.03710 0.03010 -0.1168 0.2435 1.0000
12.750 1.7163 0.03945 0.03244 -0.1145 0.2306 1.0000
13.000 1.7123 0.04209 0.03506 -0.1122 0.2165 1.0000
13.250 1.7066 0.04501 0.03797 -0.1102 0.2004 1.0000
13.500 1.6986 0.04832 0.04126 -0.1082 0.1809 1.0000
13.750 1.6852 0.05231 0.04516 -0.1063 0.1599 1.0000
14.000 1.6709 0.05653 0.04929 -0.1046 0.1384 1.0000
14.250 1.6560 0.06097 0.05364 -0.1031 0.1231 1.0000
14.500 1.6439 0.06524 0.05787 -0.1019 0.1128 1.0000
14.750 1.6337 0.06937 0.06200 -0.1009 0.1056 1.0000
15.000 1.6235 0.07360 0.06621 -0.1001 0.1003 1.0000
15.250 1.6178 0.07734 0.07000 -0.0994 0.0958 1.0000
15.500 1.6118 0.08116 0.07384 -0.0989 0.0921 1.0000
15.750 1.6044 0.08508 0.07773 -0.0983 0.0890 1.0000
16.000 1.6036 0.08829 0.08104 -0.0979 0.0859 1.0000
16.250 1.6016 0.09161 0.08438 -0.0976 0.0831 1.0000
16.500 1.5994 0.09472 0.08742 -0.0969 0.0806 1.0000
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Polar data table (+)
Polar graphs
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