SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: SOKOLOV AIRFOIL (sokolov-il) Reynolds number: 100,000 Max Cl/Cd: 68.73 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sokolov-il-100000.txt Download as CSV file: xf-sokolov-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SOKOLOV 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2984 0.10091 0.09651 -0.0269 1.0000 0.0620
-6.750 -0.3103 0.10087 0.09660 -0.0265 1.0000 0.0626
-6.500 -0.3203 0.10086 0.09672 -0.0276 1.0000 0.0630
-6.250 -0.3240 0.10039 0.09633 -0.0308 1.0000 0.0633
-6.000 -0.3288 0.09631 0.09230 -0.0261 1.0000 0.0639
-5.750 -0.3321 0.09304 0.08909 -0.0200 1.0000 0.0655
-5.500 -0.3346 0.09123 0.08733 -0.0179 1.0000 0.0677
-5.250 -0.2683 0.08730 0.08328 -0.0448 0.9918 0.0757
-5.000 -0.2640 0.08216 0.07818 -0.0376 0.9874 0.0778
-4.750 -0.2272 0.07793 0.07388 -0.0446 0.9815 0.0844
-4.500 -0.1769 0.07258 0.06844 -0.0587 0.9734 0.0899
-4.250 -0.1338 0.06856 0.06431 -0.0669 0.9674 0.0992
-4.000 -0.0972 0.06402 0.05972 -0.0734 0.9598 0.1057
-3.750 -0.0346 0.05875 0.05428 -0.0876 0.9556 0.1171
-3.500 0.0179 0.05447 0.04982 -0.0986 0.9467 0.1298
-3.250 0.0660 0.05048 0.04570 -0.1060 0.9425 0.1449
-3.000 0.1095 0.04711 0.04220 -0.1124 0.9344 0.1597
-2.750 0.1588 0.04371 0.03867 -0.1192 0.9297 0.1762
-2.000 0.3716 0.02782 0.02066 -0.1532 0.9179 0.1103
-1.750 0.4242 0.02547 0.01773 -0.1582 0.9142 0.1109
-1.500 0.4636 0.02386 0.01572 -0.1604 0.9057 0.1088
-1.250 0.5079 0.02239 0.01387 -0.1633 0.9004 0.1099
-1.000 0.5429 0.02155 0.01274 -0.1643 0.8911 0.1134
-0.750 0.5822 0.02045 0.01162 -0.1662 0.8854 0.1239
-0.500 0.6126 0.01982 0.01100 -0.1666 0.8752 0.1373
-0.250 0.6474 0.01891 0.01021 -0.1675 0.8679 0.1658
0.000 0.6803 0.01800 0.00976 -0.1681 0.8589 0.2942
0.250 0.7082 0.01739 0.00980 -0.1677 0.8485 0.5298
0.500 0.7305 0.01644 0.00943 -0.1656 0.8389 1.0000
0.750 0.7595 0.01649 0.00924 -0.1652 0.8292 1.0000
1.000 0.7862 0.01671 0.00928 -0.1647 0.8181 1.0000
1.250 0.8137 0.01688 0.00929 -0.1642 0.8080 1.0000
1.500 0.8420 0.01693 0.00920 -0.1636 0.7991 1.0000
1.750 0.8677 0.01723 0.00942 -0.1630 0.7878 1.0000
2.000 0.8944 0.01753 0.00965 -0.1626 0.7784 1.0000
2.250 0.9222 0.01769 0.00971 -0.1621 0.7703 1.0000
2.500 0.9477 0.01805 0.01008 -0.1617 0.7597 1.0000
2.750 0.9742 0.01831 0.01031 -0.1611 0.7505 1.0000
3.000 1.0014 0.01847 0.01041 -0.1606 0.7416 1.0000
3.250 1.0267 0.01879 0.01077 -0.1600 0.7307 1.0000
3.500 1.0528 0.01902 0.01104 -0.1593 0.7205 1.0000
3.750 1.0802 0.01909 0.01107 -0.1586 0.7113 1.0000
4.000 1.1054 0.01936 0.01140 -0.1579 0.6997 1.0000
4.250 1.1308 0.01966 0.01177 -0.1573 0.6889 1.0000
4.500 1.1573 0.01988 0.01208 -0.1567 0.6793 1.0000
4.750 1.1841 0.02006 0.01230 -0.1561 0.6694 1.0000
5.000 1.2091 0.02034 0.01271 -0.1553 0.6572 1.0000
5.250 1.2345 0.02055 0.01302 -0.1545 0.6445 1.0000
5.500 1.2599 0.02075 0.01335 -0.1536 0.6314 1.0000
5.750 1.2852 0.02073 0.01340 -0.1524 0.6152 1.0000
6.000 1.3097 0.02048 0.01316 -0.1507 0.5939 1.0000
6.250 1.3328 0.02019 0.01284 -0.1488 0.5678 1.0000
6.500 1.3545 0.02020 0.01302 -0.1471 0.5419 1.0000
6.750 1.3751 0.02015 0.01300 -0.1450 0.5095 1.0000
7.000 1.3897 0.02022 0.01303 -0.1419 0.4457 1.0000
7.250 1.3948 0.02143 0.01346 -0.1376 0.3301 1.0000
7.500 1.3847 0.02487 0.01552 -0.1323 0.1545 1.0000
7.750 1.3820 0.02793 0.01785 -0.1278 0.0726 1.0000
8.000 1.3874 0.02992 0.01984 -0.1243 0.0612 1.0000
8.250 1.3885 0.03201 0.02197 -0.1205 0.0550 1.0000
8.500 1.3931 0.03363 0.02379 -0.1170 0.0511 1.0000
8.750 1.3939 0.03543 0.02573 -0.1131 0.0488 1.0000
9.000 1.3952 0.03743 0.02780 -0.1096 0.0471 1.0000
9.250 1.3984 0.03962 0.03002 -0.1064 0.0455 1.0000
9.500 1.4114 0.04215 0.03248 -0.1041 0.0440 1.0000
9.750 1.4419 0.04454 0.03491 -0.1035 0.0427 1.0000
10.000 1.4655 0.04662 0.03723 -0.1025 0.0408 1.0000
10.250 1.4978 0.04959 0.04049 -0.1027 0.0396 1.0000
10.500 1.5281 0.05345 0.04471 -0.1027 0.0399 1.0000
10.750 1.5450 0.05746 0.04913 -0.1012 0.0405 1.0000
11.000 1.5542 0.06176 0.05382 -0.0990 0.0414 1.0000
11.250 1.5598 0.06669 0.05911 -0.0968 0.0424 1.0000
11.500 1.5752 0.07237 0.06506 -0.0959 0.0440 1.0000
11.750 1.5587 0.07350 0.06664 -0.0902 0.0454 1.0000
12.000 1.5263 0.07659 0.07021 -0.0847 0.0464 1.0000
12.250 1.4973 0.08109 0.07516 -0.0813 0.0477 1.0000
12.500 1.4717 0.08623 0.08064 -0.0794 0.0489 1.0000
12.750 1.4476 0.09171 0.08640 -0.0788 0.0499 1.0000
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Polar data table (+)
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