USA 98 AIRFOIL (usa98-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 98 AIRFOIL (usa98-il) Reynolds number: 100,000 Max Cl/Cd: 59.73 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa98-il-100000-n5.txt Download as CSV file: xf-usa98-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.0770 0.09984 0.09420 -0.0790 0.9264 0.0983
-7.500 -0.0908 0.09746 0.09183 -0.0860 0.9086 0.1019
-7.250 -0.0850 0.09376 0.08813 -0.0903 0.8978 0.1024
-7.000 -0.0578 0.09011 0.08447 -0.0902 0.8923 0.1032
-6.750 -0.0325 0.08685 0.08117 -0.0919 0.8869 0.1042
-6.500 -0.0150 0.08403 0.07834 -0.0935 0.8780 0.1053
-6.000 0.0011 0.06979 0.06384 -0.1130 0.8579 0.0812
-5.750 0.0272 0.06728 0.06129 -0.1152 0.8525 0.0818
-5.250 0.0820 0.04506 0.03825 -0.1499 0.8360 0.0718
-5.000 0.1191 0.03993 0.03267 -0.1586 0.8303 0.0716
-4.750 0.1536 0.03584 0.02804 -0.1652 0.8226 0.0724
-4.500 0.1867 0.03431 0.02645 -0.1675 0.8166 0.0732
-4.250 0.2215 0.03239 0.02426 -0.1707 0.8106 0.0739
-4.000 0.2530 0.03051 0.02207 -0.1731 0.8031 0.0742
-3.750 0.2881 0.02886 0.02007 -0.1757 0.7970 0.0746
-3.500 0.3220 0.02754 0.01846 -0.1776 0.7910 0.0751
-3.250 0.3512 0.02654 0.01725 -0.1785 0.7835 0.0757
-3.000 0.3838 0.02561 0.01608 -0.1798 0.7772 0.0765
-2.750 0.4160 0.02486 0.01510 -0.1809 0.7714 0.0781
-2.500 0.4440 0.02429 0.01434 -0.1811 0.7638 0.0796
-2.250 0.4752 0.02372 0.01353 -0.1817 0.7575 0.0807
-2.000 0.5065 0.02307 0.01282 -0.1824 0.7521 0.0816
-1.750 0.5323 0.02267 0.01244 -0.1821 0.7445 0.0826
-1.500 0.5615 0.02226 0.01200 -0.1824 0.7381 0.0838
-1.250 0.5929 0.02188 0.01155 -0.1829 0.7331 0.0853
-1.000 0.6180 0.02169 0.01139 -0.1824 0.7254 0.0874
-0.750 0.6464 0.02149 0.01113 -0.1824 0.7189 0.0901
-0.500 0.6771 0.02118 0.01082 -0.1828 0.7138 0.0926
-0.250 0.7028 0.02105 0.01077 -0.1824 0.7067 0.0949
0.000 0.7306 0.02092 0.01063 -0.1823 0.7000 0.0977
0.250 0.7611 0.02077 0.01040 -0.1827 0.6947 0.1011
0.500 0.7875 0.02069 0.01038 -0.1824 0.6880 0.1060
0.750 0.8149 0.02064 0.01034 -0.1823 0.6812 0.1135
1.000 0.8453 0.02046 0.01016 -0.1827 0.6758 0.1248
1.250 0.8731 0.02027 0.01016 -0.1827 0.6695 0.1570
1.500 0.8998 0.02009 0.01056 -0.1827 0.6626 0.3335
1.750 0.9284 0.02018 0.01070 -0.1826 0.6570 0.3924
2.000 0.9550 0.02034 0.01091 -0.1822 0.6510 0.4283
2.250 0.9796 0.02053 0.01119 -0.1814 0.6439 0.4604
2.500 1.0071 0.02060 0.01132 -0.1811 0.6382 0.5033
2.750 1.0334 0.02067 0.01149 -0.1806 0.6325 0.5398
3.000 1.0571 0.02083 0.01174 -0.1797 0.6252 0.5645
3.500 1.1102 0.02090 0.01195 -0.1788 0.6135 0.6229
3.750 1.1316 0.02094 0.01224 -0.1774 0.6061 0.6874
4.000 1.1534 0.02059 0.01213 -0.1757 0.6001 1.0000
4.250 1.1783 0.02086 0.01233 -0.1750 0.5924 1.0000
4.500 1.2028 0.02108 0.01248 -0.1742 0.5836 1.0000
4.750 1.2288 0.02126 0.01256 -0.1736 0.5756 1.0000
5.000 1.2509 0.02156 0.01285 -0.1724 0.5664 1.0000
5.250 1.2792 0.02171 0.01288 -0.1722 0.5599 1.0000
5.500 1.2987 0.02215 0.01338 -0.1707 0.5513 1.0000
5.750 1.3236 0.02240 0.01359 -0.1700 0.5441 1.0000
6.000 1.3467 0.02274 0.01392 -0.1690 0.5368 1.0000
6.250 1.3677 0.02312 0.01432 -0.1677 0.5286 1.0000
6.500 1.3942 0.02334 0.01446 -0.1673 0.5220 1.0000
6.750 1.4112 0.02386 0.01507 -0.1653 0.5131 1.0000
7.000 1.4346 0.02415 0.01533 -0.1643 0.5056 1.0000
7.250 1.4527 0.02462 0.01587 -0.1626 0.4970 1.0000
7.500 1.4726 0.02501 0.01627 -0.1610 0.4886 1.0000
7.750 1.4915 0.02546 0.01674 -0.1594 0.4804 1.0000
8.000 1.5078 0.02595 0.01728 -0.1573 0.4714 1.0000
8.250 1.5248 0.02640 0.01775 -0.1553 0.4622 1.0000
8.500 1.5371 0.02692 0.01830 -0.1525 0.4517 1.0000
8.750 1.5468 0.02751 0.01894 -0.1493 0.4409 1.0000
9.000 1.5599 0.02802 0.01941 -0.1467 0.4301 1.0000
9.250 1.5656 0.02886 0.02034 -0.1431 0.4179 1.0000
9.500 1.5737 0.02964 0.02113 -0.1400 0.4057 1.0000
9.750 1.5825 0.03044 0.02188 -0.1370 0.3937 1.0000
10.000 1.5868 0.03155 0.02307 -0.1337 0.3809 1.0000
10.250 1.5923 0.03266 0.02422 -0.1307 0.3685 1.0000
10.500 1.5976 0.03384 0.02537 -0.1278 0.3563 1.0000
10.750 1.6005 0.03526 0.02681 -0.1248 0.3432 1.0000
11.000 1.6027 0.03683 0.02841 -0.1220 0.3300 1.0000
11.250 1.6045 0.03853 0.03010 -0.1194 0.3173 1.0000
11.500 1.6056 0.04035 0.03190 -0.1169 0.3050 1.0000
11.750 1.6065 0.04234 0.03393 -0.1146 0.2930 1.0000
12.000 1.6082 0.04436 0.03598 -0.1126 0.2825 1.0000
12.250 1.6088 0.04649 0.03809 -0.1105 0.2723 1.0000
12.500 1.6091 0.04878 0.04046 -0.1087 0.2619 1.0000
12.750 1.6085 0.05118 0.04288 -0.1069 0.2521 1.0000
13.000 1.6071 0.05376 0.04550 -0.1053 0.2418 1.0000
13.250 1.6056 0.05645 0.04824 -0.1039 0.2320 1.0000
13.500 1.6022 0.05933 0.05112 -0.1024 0.2222 1.0000
13.750 1.5991 0.06240 0.05428 -0.1013 0.2117 1.0000
14.000 1.5946 0.06565 0.05757 -0.1002 0.2014 1.0000
14.250 1.5880 0.06921 0.06116 -0.0992 0.1907 1.0000
14.500 1.5821 0.07289 0.06493 -0.0986 0.1789 1.0000
14.750 1.5747 0.07683 0.06892 -0.0980 0.1670 1.0000
15.000 1.5658 0.08105 0.07317 -0.0977 0.1548 1.0000
15.250 1.5559 0.08551 0.07763 -0.0975 0.1430 1.0000
15.500 1.5453 0.09016 0.08227 -0.0976 0.1321 1.0000
15.750 1.5357 0.09475 0.08687 -0.0978 0.1222 1.0000
16.000 1.5271 0.09927 0.09141 -0.0981 0.1142 1.0000
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Polar data table (+)
Polar graphs
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