USA 98 AIRFOIL (usa98-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 98 AIRFOIL (usa98-il) Reynolds number: 500,000 Max Cl/Cd: 120.34 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa98-il-500000.txt Download as CSV file: xf-usa98-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.0843 0.09823 0.09555 -0.0854 0.9743 0.0496
-8.750 -0.0639 0.09470 0.09201 -0.0899 0.9711 0.0505
-8.250 -0.0592 0.08358 0.08086 -0.1021 0.9490 0.0535
-8.000 -0.0387 0.08114 0.07841 -0.1037 0.9351 0.0537
-7.750 -0.0124 0.07837 0.07561 -0.1071 0.9166 0.0540
-7.500 0.0154 0.07536 0.07249 -0.1114 0.8889 0.0545
-7.250 0.0315 0.07290 0.06982 -0.1135 0.8562 0.0551
-7.000 0.0126 0.06179 0.05848 -0.1310 0.8294 0.0591
-6.750 0.0272 0.06049 0.05713 -0.1297 0.8186 0.0594
-6.500 0.0435 0.05916 0.05573 -0.1296 0.8090 0.0596
-6.250 0.0608 0.05771 0.05424 -0.1302 0.8009 0.0600
-6.000 0.0892 0.03811 0.03411 -0.1667 0.7922 0.0661
-5.750 0.1119 0.03683 0.03280 -0.1670 0.7856 0.0664
-5.500 0.1355 0.03553 0.03151 -0.1677 0.7794 0.0669
-5.250 0.1606 0.03400 0.02992 -0.1693 0.7729 0.0675
-5.000 0.1879 0.03204 0.02780 -0.1719 0.7669 0.0686
-4.750 0.2235 0.02692 0.02201 -0.1799 0.7616 0.0740
-4.500 0.2607 0.01961 0.01346 -0.1852 0.7565 0.0592
-4.250 0.2899 0.01879 0.01249 -0.1858 0.7507 0.0590
-4.000 0.3195 0.01778 0.01128 -0.1864 0.7451 0.0590
-3.750 0.3488 0.01674 0.01011 -0.1870 0.7399 0.0591
-3.500 0.3779 0.01561 0.00889 -0.1876 0.7343 0.0595
-3.250 0.4069 0.01499 0.00822 -0.1879 0.7287 0.0603
-3.000 0.4360 0.01462 0.00781 -0.1882 0.7232 0.0610
-2.750 0.4651 0.01418 0.00734 -0.1884 0.7177 0.0615
-2.500 0.4942 0.01379 0.00689 -0.1886 0.7120 0.0620
-2.250 0.5235 0.01348 0.00649 -0.1888 0.7064 0.0626
-2.000 0.5526 0.01314 0.00614 -0.1889 0.7008 0.0633
-1.750 0.5816 0.01285 0.00582 -0.1890 0.6949 0.0640
-1.500 0.6107 0.01264 0.00554 -0.1891 0.6892 0.0647
-1.250 0.6398 0.01250 0.00534 -0.1892 0.6834 0.0654
-1.000 0.6687 0.01207 0.00495 -0.1894 0.6773 0.0667
-0.750 0.6976 0.01188 0.00477 -0.1895 0.6713 0.0681
-0.500 0.7267 0.01179 0.00464 -0.1897 0.6655 0.0694
-0.250 0.7554 0.01163 0.00451 -0.1897 0.6592 0.0707
0.000 0.7842 0.01153 0.00438 -0.1897 0.6528 0.0721
0.250 0.8132 0.01145 0.00424 -0.1898 0.6468 0.0736
0.500 0.8420 0.01128 0.00413 -0.1899 0.6405 0.0759
0.750 0.8705 0.01123 0.00407 -0.1899 0.6339 0.0786
1.000 0.8991 0.01124 0.00402 -0.1899 0.6277 0.0819
1.250 0.9277 0.01113 0.00398 -0.1900 0.6213 0.0867
1.500 0.9561 0.01108 0.00393 -0.1899 0.6146 0.0943
1.750 0.9854 0.01072 0.00395 -0.1904 0.6083 0.2492
2.000 1.0133 0.01060 0.00410 -0.1904 0.6010 0.3499
2.250 1.0404 0.01067 0.00419 -0.1901 0.5928 0.3842
2.500 1.0674 0.01074 0.00429 -0.1898 0.5842 0.4075
2.750 1.0942 0.01082 0.00437 -0.1894 0.5758 0.4280
3.000 1.1213 0.01093 0.00449 -0.1891 0.5690 0.4477
3.250 1.1485 0.01099 0.00462 -0.1889 0.5619 0.4687
3.500 1.1751 0.01111 0.00474 -0.1885 0.5551 0.4900
3.750 1.2021 0.01118 0.00488 -0.1883 0.5489 0.5131
4.000 1.2289 0.01124 0.00502 -0.1880 0.5420 0.5429
4.250 1.2549 0.01132 0.00518 -0.1875 0.5351 0.5880
4.500 1.2808 0.01114 0.00540 -0.1871 0.5287 0.7347
4.750 1.3011 0.01087 0.00545 -0.1852 0.5222 1.0000
5.000 1.3265 0.01111 0.00560 -0.1846 0.5152 1.0000
5.250 1.3523 0.01124 0.00575 -0.1841 0.5069 1.0000
5.500 1.3766 0.01149 0.00591 -0.1833 0.4983 1.0000
5.750 1.4019 0.01165 0.00608 -0.1827 0.4901 1.0000
6.000 1.4257 0.01188 0.00626 -0.1818 0.4815 1.0000
6.250 1.4501 0.01208 0.00647 -0.1810 0.4736 1.0000
6.500 1.4735 0.01231 0.00667 -0.1801 0.4647 1.0000
6.750 1.4963 0.01255 0.00689 -0.1790 0.4552 1.0000
7.000 1.5177 0.01283 0.00713 -0.1777 0.4446 1.0000
7.250 1.5400 0.01308 0.00738 -0.1765 0.4350 1.0000
7.500 1.5592 0.01343 0.00767 -0.1748 0.4243 1.0000
7.750 1.5796 0.01371 0.00795 -0.1733 0.4117 1.0000
8.000 1.5973 0.01407 0.00828 -0.1713 0.3986 1.0000
8.250 1.6121 0.01450 0.00866 -0.1687 0.3850 1.0000
8.500 1.6260 0.01501 0.00910 -0.1660 0.3699 1.0000
8.750 1.6396 0.01557 0.00960 -0.1634 0.3535 1.0000
9.000 1.6522 0.01620 0.01016 -0.1606 0.3362 1.0000
9.250 1.6640 0.01690 0.01078 -0.1578 0.3177 1.0000
9.500 1.6742 0.01769 0.01150 -0.1548 0.2989 1.0000
9.750 1.6840 0.01854 0.01228 -0.1519 0.2820 1.0000
10.000 1.6930 0.01947 0.01313 -0.1489 0.2669 1.0000
10.250 1.7022 0.02042 0.01403 -0.1460 0.2529 1.0000
10.500 1.7121 0.02136 0.01495 -0.1434 0.2402 1.0000
10.750 1.7208 0.02242 0.01597 -0.1406 0.2286 1.0000
11.000 1.7276 0.02362 0.01714 -0.1378 0.2169 1.0000
11.250 1.7341 0.02491 0.01840 -0.1351 0.2047 1.0000
11.500 1.7409 0.02625 0.01972 -0.1326 0.1917 1.0000
11.750 1.7448 0.02788 0.02129 -0.1300 0.1766 1.0000
12.000 1.7445 0.02992 0.02325 -0.1271 0.1582 1.0000
12.250 1.7387 0.03254 0.02574 -0.1241 0.1330 1.0000
12.500 1.7278 0.03576 0.02879 -0.1210 0.1066 1.0000
12.750 1.7192 0.03891 0.03185 -0.1184 0.0906 1.0000
13.000 1.7155 0.04174 0.03466 -0.1163 0.0822 1.0000
13.250 1.7145 0.04437 0.03731 -0.1145 0.0771 1.0000
13.500 1.7122 0.04718 0.04014 -0.1128 0.0733 1.0000
13.750 1.7126 0.04979 0.04281 -0.1114 0.0704 1.0000
14.000 1.7125 0.05250 0.04557 -0.1101 0.0679 1.0000
14.250 1.7092 0.05561 0.04872 -0.1087 0.0657 1.0000
14.500 1.7077 0.05858 0.05176 -0.1076 0.0638 1.0000
14.750 1.7089 0.06130 0.05456 -0.1066 0.0620 1.0000
15.000 1.7073 0.06442 0.05774 -0.1057 0.0603 1.0000
15.250 1.7028 0.06793 0.06130 -0.1049 0.0588 1.0000
15.500 1.6966 0.07169 0.06513 -0.1041 0.0574 1.0000
15.750 1.6981 0.07457 0.06810 -0.1035 0.0562 1.0000
16.000 1.6973 0.07777 0.07139 -0.1031 0.0549 1.0000
16.250 1.6953 0.08115 0.07483 -0.1027 0.0536 1.0000
16.500 1.6897 0.08503 0.07876 -0.1024 0.0524 1.0000
16.750 1.6806 0.08938 0.08317 -0.1021 0.0513 1.0000
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