SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SOKOLOV AIRFOIL (sokolov-il) Reynolds number: 100,000 Max Cl/Cd: 69.55 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sokolov-il-100000-n5.txt Download as CSV file: xf-sokolov-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2705 0.10239 0.09785 -0.0309 1.0000 0.0353
-7.250 -0.2777 0.10108 0.09664 -0.0288 1.0000 0.0362
-7.000 -0.2819 0.09959 0.09524 -0.0279 0.9980 0.0377
-6.750 -0.2510 0.09653 0.09217 -0.0421 0.9862 0.0406
-6.500 -0.2191 0.09225 0.08786 -0.0532 0.9774 0.0410
-6.250 -0.1900 0.08749 0.08307 -0.0613 0.9693 0.0411
-6.000 -0.1642 0.08180 0.07738 -0.0671 0.9639 0.0414
-5.750 -0.1529 0.07737 0.07295 -0.0650 0.9574 0.0427
-5.500 -0.1260 0.07331 0.06884 -0.0691 0.9523 0.0444
-5.250 -0.0712 0.06896 0.06435 -0.0876 0.9409 0.0538
-4.750 -0.0138 0.05772 0.05298 -0.0977 0.9256 0.0428
-4.250 0.0589 0.04985 0.04489 -0.1103 0.9097 0.0480
-4.000 0.1123 0.04333 0.03810 -0.1223 0.9011 0.0460
-3.750 0.1708 0.03731 0.03168 -0.1340 0.8956 0.0503
-3.500 0.2282 0.03088 0.02461 -0.1444 0.8882 0.0509
-3.250 0.2818 0.02601 0.01880 -0.1521 0.8823 0.0545
-3.000 0.3196 0.02351 0.01580 -0.1551 0.8733 0.0551
-2.750 0.3568 0.02156 0.01337 -0.1574 0.8658 0.0557
-2.500 0.3903 0.02021 0.01166 -0.1587 0.8563 0.0569
-2.250 0.4226 0.01917 0.01033 -0.1595 0.8468 0.0585
-2.000 0.4545 0.01831 0.00922 -0.1602 0.8381 0.0604
-1.750 0.4846 0.01773 0.00842 -0.1605 0.8281 0.0645
-1.500 0.5143 0.01727 0.00786 -0.1608 0.8184 0.0687
-1.250 0.5440 0.01684 0.00734 -0.1610 0.8101 0.0710
-1.000 0.5729 0.01653 0.00694 -0.1611 0.8000 0.0737
-0.750 0.6020 0.01629 0.00658 -0.1612 0.7906 0.0778
-0.500 0.6312 0.01612 0.00636 -0.1612 0.7820 0.0860
-0.250 0.6598 0.01598 0.00615 -0.1613 0.7721 0.1050
0.000 0.6885 0.01581 0.00594 -0.1613 0.7631 0.1349
0.250 0.7167 0.01566 0.00586 -0.1613 0.7535 0.1776
0.500 0.7442 0.01544 0.00600 -0.1614 0.7427 0.2992
0.750 0.7713 0.01527 0.00613 -0.1611 0.7325 0.4504
1.000 0.7974 0.01491 0.00613 -0.1606 0.7233 0.5922
1.250 0.8191 0.01447 0.00606 -0.1590 0.7130 1.0000
1.500 0.8467 0.01464 0.00609 -0.1588 0.7037 1.0000
1.750 0.8742 0.01481 0.00612 -0.1586 0.6947 1.0000
2.000 0.9012 0.01501 0.00625 -0.1583 0.6842 1.0000
2.250 0.9282 0.01518 0.00634 -0.1580 0.6740 1.0000
2.500 0.9553 0.01536 0.00643 -0.1577 0.6649 1.0000
2.750 0.9821 0.01558 0.00663 -0.1575 0.6548 1.0000
3.000 1.0089 0.01579 0.00682 -0.1572 0.6456 1.0000
3.250 1.0357 0.01599 0.00699 -0.1569 0.6364 1.0000
3.500 1.0622 0.01623 0.00726 -0.1566 0.6264 1.0000
3.750 1.0887 0.01646 0.00752 -0.1562 0.6168 1.0000
4.000 1.1151 0.01669 0.00776 -0.1558 0.6072 1.0000
4.250 1.1411 0.01695 0.00810 -0.1555 0.5968 1.0000
4.500 1.1674 0.01721 0.00845 -0.1551 0.5879 1.0000
4.750 1.1934 0.01748 0.00879 -0.1547 0.5786 1.0000
5.000 1.2191 0.01777 0.00920 -0.1543 0.5680 1.0000
5.250 1.2447 0.01807 0.00960 -0.1538 0.5575 1.0000
5.500 1.2701 0.01836 0.01003 -0.1532 0.5468 1.0000
5.750 1.2942 0.01865 0.01044 -0.1524 0.5297 1.0000
6.000 1.3151 0.01891 0.01070 -0.1509 0.4955 1.0000
6.250 1.3340 0.01930 0.01099 -0.1491 0.4454 1.0000
6.500 1.3514 0.01995 0.01142 -0.1471 0.3831 1.0000
6.750 1.3654 0.02106 0.01223 -0.1448 0.3267 1.0000
7.250 1.3681 0.02600 0.01555 -0.1376 0.0890 1.0000
7.500 1.3685 0.02853 0.01754 -0.1338 0.0347 1.0000
7.750 1.3790 0.02998 0.01908 -0.1311 0.0288 1.0000
8.000 1.3871 0.03153 0.02074 -0.1282 0.0255 1.0000
8.250 1.3952 0.03294 0.02235 -0.1253 0.0232 1.0000
8.500 1.3991 0.03447 0.02409 -0.1219 0.0219 1.0000
8.750 1.4016 0.03622 0.02603 -0.1185 0.0210 1.0000
9.000 1.4027 0.03818 0.02818 -0.1153 0.0203 1.0000
9.250 1.4025 0.04036 0.03054 -0.1123 0.0196 1.0000
9.500 1.4012 0.04277 0.03317 -0.1095 0.0188 1.0000
9.750 1.3987 0.04546 0.03599 -0.1069 0.0180 1.0000
10.000 1.3957 0.04844 0.03909 -0.1043 0.0171 1.0000
10.250 1.3991 0.05106 0.04179 -0.1020 0.0164 1.0000
10.500 1.4076 0.05324 0.04412 -0.1001 0.0160 1.0000
10.750 1.4184 0.05547 0.04651 -0.0981 0.0157 1.0000
11.000 1.4302 0.05783 0.04906 -0.0963 0.0154 1.0000
11.250 1.4421 0.06040 0.05185 -0.0945 0.0151 1.0000
11.500 1.4519 0.06327 0.05497 -0.0927 0.0149 1.0000
11.750 1.4574 0.06640 0.05839 -0.0911 0.0147 1.0000
12.000 1.4583 0.06976 0.06204 -0.0895 0.0143 1.0000
12.250 1.4556 0.07336 0.06593 -0.0882 0.0140 1.0000
12.500 1.4500 0.07722 0.07007 -0.0872 0.0136 1.0000
12.750 1.4420 0.08138 0.07451 -0.0865 0.0134 1.0000
13.000 1.4321 0.08587 0.07928 -0.0862 0.0132 1.0000
13.250 1.4203 0.09069 0.08437 -0.0863 0.0130 1.0000
13.500 1.4071 0.09587 0.08982 -0.0870 0.0130 1.0000
13.750 1.3927 0.10145 0.09566 -0.0882 0.0129 1.0000
14.000 1.3772 0.10742 0.10189 -0.0901 0.0129 1.0000
14.250 1.3613 0.11387 0.10858 -0.0927 0.0130 1.0000
14.500 1.3449 0.12088 0.11583 -0.0962 0.0130 1.0000
14.750 1.3283 0.12846 0.12362 -0.1004 0.0131 1.0000
15.000 1.3117 0.13670 0.13207 -0.1055 0.0133 1.0000
15.250 1.2951 0.14570 0.14126 -0.1115 0.0134 1.0000
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