FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il) Reynolds number: 100,000 Max Cl/Cd: 47.35 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxs21158-il-100000-n5.txt Download as CSV file: xf-fxs21158-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX S 02/1-158 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3717 0.09215 0.08777 -0.0472 1.0000 0.0314
-10.500 -0.3840 0.08436 0.08003 -0.0518 1.0000 0.0314
-10.250 -0.4001 0.07729 0.07299 -0.0564 1.0000 0.0313
-10.000 -0.4192 0.07100 0.06670 -0.0607 1.0000 0.0312
-9.750 -0.4380 0.06582 0.06151 -0.0640 1.0000 0.0310
-9.250 -0.4498 0.05204 0.04677 -0.0845 0.8336 0.0323
-8.750 -0.4312 0.04680 0.04101 -0.0867 0.7666 0.0351
-8.500 -0.4256 0.04370 0.03748 -0.0872 0.7437 0.0357
-8.250 -0.4153 0.04092 0.03424 -0.0873 0.7250 0.0365
-8.000 -0.4009 0.03877 0.03166 -0.0874 0.7085 0.0385
-7.750 -0.3843 0.03649 0.02885 -0.0874 0.6938 0.0398
-7.500 -0.3650 0.03421 0.02612 -0.0873 0.6812 0.0402
-7.250 -0.3433 0.03226 0.02375 -0.0871 0.6699 0.0407
-7.000 -0.3197 0.03054 0.02166 -0.0869 0.6597 0.0412
-6.750 -0.2952 0.02908 0.01989 -0.0867 0.6505 0.0417
-6.500 -0.2701 0.02780 0.01835 -0.0864 0.6412 0.0423
-6.250 -0.2452 0.02662 0.01697 -0.0861 0.6335 0.0436
-6.000 -0.2210 0.02549 0.01581 -0.0859 0.6258 0.0455
-5.750 -0.1962 0.02463 0.01482 -0.0855 0.6193 0.0470
-5.500 -0.1716 0.02382 0.01393 -0.0849 0.6123 0.0478
-5.250 -0.1473 0.02312 0.01313 -0.0843 0.6067 0.0489
-5.000 -0.1230 0.02250 0.01246 -0.0838 0.6003 0.0502
-4.750 -0.0984 0.02196 0.01180 -0.0835 0.5950 0.0518
-4.500 -0.0730 0.02147 0.01115 -0.0833 0.5904 0.0539
-4.250 -0.0474 0.02089 0.01046 -0.0834 0.5853 0.0569
-4.000 -0.0209 0.02039 0.00979 -0.0837 0.5807 0.0627
-3.750 0.0060 0.01977 0.00907 -0.0840 0.5764 0.0736
-3.500 0.0323 0.01865 0.00828 -0.0850 0.5712 0.1508
-3.250 0.0562 0.01796 0.00874 -0.0853 0.5668 0.4545
-3.000 0.0828 0.01876 0.00941 -0.0844 0.5631 0.5018
-2.750 0.1078 0.01949 0.01017 -0.0830 0.5587 0.5317
-2.500 0.1350 0.01969 0.01022 -0.0826 0.5550 0.5438
-2.250 0.1626 0.01973 0.01010 -0.0825 0.5517 0.5489
-2.000 0.1913 0.01977 0.00987 -0.0829 0.5489 0.5564
-1.750 0.2178 0.01988 0.00998 -0.0825 0.5451 0.5625
-1.500 0.2460 0.01994 0.00989 -0.0827 0.5415 0.5702
-1.250 0.2734 0.01998 0.00983 -0.0826 0.5384 0.5742
-1.000 0.3015 0.02000 0.00972 -0.0828 0.5358 0.5773
-0.750 0.3299 0.02003 0.00964 -0.0831 0.5332 0.5802
-0.500 0.3581 0.02008 0.00962 -0.0835 0.5301 0.5835
-0.250 0.3864 0.02014 0.00960 -0.0839 0.5272 0.5861
0.000 0.4141 0.02021 0.00962 -0.0841 0.5247 0.5881
0.250 0.4422 0.02028 0.00962 -0.0843 0.5224 0.5903
0.500 0.4705 0.02038 0.00963 -0.0845 0.5205 0.5931
0.750 0.4980 0.02053 0.00979 -0.0848 0.5178 0.5963
1.000 0.5257 0.02070 0.00995 -0.0851 0.5151 0.5996
1.250 0.5530 0.02086 0.01012 -0.0853 0.5126 0.6020
1.500 0.5804 0.02101 0.01027 -0.0854 0.5102 0.6045
1.750 0.6081 0.02115 0.01039 -0.0856 0.5080 0.6075
2.000 0.6363 0.02131 0.01050 -0.0858 0.5061 0.6111
2.250 0.6630 0.02158 0.01082 -0.0860 0.5034 0.6149
2.500 0.6889 0.02185 0.01119 -0.0860 0.5008 0.6177
2.750 0.7153 0.02211 0.01154 -0.0861 0.4985 0.6209
3.000 0.7423 0.02238 0.01184 -0.0862 0.4964 0.6245
3.250 0.7696 0.02264 0.01212 -0.0864 0.4945 0.6289
3.500 0.7968 0.02288 0.01240 -0.0865 0.4929 0.6326
3.750 0.8237 0.02315 0.01274 -0.0865 0.4910 0.6369
4.000 0.8476 0.02361 0.01336 -0.0864 0.4873 0.6416
4.250 0.8730 0.02393 0.01379 -0.0863 0.4839 0.6460
4.500 0.8995 0.02419 0.01412 -0.0863 0.4813 0.6506
4.750 0.9270 0.02443 0.01443 -0.0865 0.4791 0.6562
5.000 0.9548 0.02467 0.01472 -0.0866 0.4774 0.6621
5.250 0.9763 0.02530 0.01559 -0.0862 0.4740 0.6687
5.500 0.9990 0.02587 0.01635 -0.0859 0.4709 0.6761
5.750 1.0234 0.02629 0.01695 -0.0857 0.4681 0.6844
6.000 1.0493 0.02657 0.01737 -0.0856 0.4657 0.6936
6.250 1.0765 0.02680 0.01770 -0.0856 0.4637 0.7046
6.500 1.0969 0.02739 0.01854 -0.0850 0.4600 0.7174
6.750 1.1164 0.02778 0.01920 -0.0841 0.4544 0.7343
7.000 1.1454 0.02724 0.01880 -0.0837 0.4496 0.7602
7.250 1.1596 0.02746 0.01942 -0.0817 0.4426 0.8123
7.500 1.1871 0.02680 0.01890 -0.0812 0.4360 1.0000
7.750 1.2072 0.02719 0.01944 -0.0805 0.4295 1.0000
8.000 1.2301 0.02742 0.01978 -0.0800 0.4241 1.0000
8.250 1.2601 0.02715 0.01953 -0.0800 0.4200 1.0000
8.500 1.2716 0.02807 0.02076 -0.0785 0.4128 1.0000
8.750 1.3006 0.02747 0.02017 -0.0781 0.4054 1.0000
9.000 1.3097 0.02804 0.02097 -0.0760 0.3935 1.0000
9.250 1.3185 0.02859 0.02171 -0.0739 0.3804 1.0000
9.500 1.3255 0.02926 0.02254 -0.0716 0.3668 1.0000
9.750 1.3300 0.02984 0.02320 -0.0688 0.3520 1.0000
10.000 1.3270 0.03115 0.02461 -0.0659 0.3388 1.0000
10.250 1.3089 0.03399 0.02759 -0.0631 0.3250 1.0000
10.500 1.2772 0.03916 0.03291 -0.0619 0.3178 1.0000
10.750 1.2365 0.04662 0.04055 -0.0623 0.3171 1.0000
11.000 1.2134 0.05218 0.04619 -0.0627 0.3040 1.0000
11.250 1.2536 0.04800 0.04108 -0.0598 0.2215 1.0000
11.500 1.2328 0.05298 0.04594 -0.0598 0.1903 1.0000
11.750 1.2138 0.05789 0.05074 -0.0599 0.1756 1.0000
12.000 1.1957 0.06283 0.05558 -0.0602 0.1450 1.0000
12.250 1.1750 0.06822 0.06077 -0.0608 0.1297 1.0000
12.500 1.1674 0.07230 0.06483 -0.0613 0.1033 1.0000
12.750 1.1527 0.07739 0.06974 -0.0621 0.0886 1.0000
13.000 1.1495 0.08115 0.07356 -0.0627 0.0677 1.0000
13.250 1.1405 0.08576 0.07801 -0.0636 0.0559 1.0000
13.500 1.1381 0.08955 0.08180 -0.0644 0.0460 1.0000
13.750 1.1336 0.09369 0.08584 -0.0653 0.0348 1.0000
14.000 1.1320 0.09751 0.08966 -0.0661 0.0289 1.0000
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Polar data table (+)
Polar graphs
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