FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il) Reynolds number: 50,000 Max Cl/Cd: 18.36 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxs21158-il-50000-n5.txt Download as CSV file: xf-fxs21158-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3434 0.10352 0.09730 -0.0432 1.0000 0.0630
-10.250 -0.3475 0.09848 0.09237 -0.0459 1.0000 0.0634
-10.000 -0.3525 0.09319 0.08717 -0.0487 1.0000 0.0633
-9.750 -0.3591 0.08759 0.08167 -0.0518 1.0000 0.0627
-9.500 -0.3700 0.08187 0.07606 -0.0552 1.0000 0.0618
-9.250 -0.3881 0.07612 0.07043 -0.0588 1.0000 0.0609
-9.000 -0.4124 0.07126 0.06569 -0.0615 1.0000 0.0599
-8.750 -0.4328 0.06571 0.06021 -0.0675 0.9652 0.0590
-8.500 -0.4275 0.05890 0.05294 -0.0771 0.9145 0.0586
-8.250 -0.4131 0.05343 0.04686 -0.0833 0.8799 0.0584
-8.000 -0.3955 0.04917 0.04201 -0.0870 0.8508 0.0587
-7.750 -0.3767 0.04577 0.03805 -0.0888 0.8259 0.0591
-7.500 -0.3573 0.04299 0.03474 -0.0895 0.8042 0.0599
-7.250 -0.3368 0.04080 0.03204 -0.0898 0.7857 0.0622
-7.000 -0.3154 0.03887 0.02951 -0.0898 0.7695 0.0648
-6.750 -0.2919 0.03716 0.02728 -0.0894 0.7548 0.0660
-6.500 -0.2668 0.03545 0.02532 -0.0887 0.7416 0.0669
-6.250 -0.2414 0.03406 0.02380 -0.0878 0.7296 0.0681
-6.000 -0.2162 0.03300 0.02254 -0.0866 0.7188 0.0697
-5.750 -0.1918 0.03214 0.02152 -0.0853 0.7089 0.0716
-5.500 -0.1688 0.03140 0.02065 -0.0840 0.6993 0.0738
-5.250 -0.1464 0.03072 0.01978 -0.0828 0.6916 0.0766
-5.000 -0.1254 0.02998 0.01897 -0.0820 0.6836 0.0798
-4.750 -0.1037 0.02921 0.01811 -0.0818 0.6769 0.0861
-4.500 -0.0818 0.02839 0.01725 -0.0818 0.6695 0.0971
-4.250 -0.0586 0.02732 0.01609 -0.0823 0.6637 0.1134
-4.000 -0.0363 0.02542 0.01472 -0.0841 0.6567 0.1730
-3.750 -0.0178 0.02617 0.01661 -0.0816 0.6511 0.4846
-3.500 0.0014 0.02788 0.01828 -0.0777 0.6451 0.5427
-3.250 0.0184 0.02920 0.01960 -0.0729 0.6397 0.5825
-3.000 0.0414 0.02953 0.01968 -0.0709 0.6355 0.6024
-2.750 0.0649 0.02964 0.01962 -0.0703 0.6296 0.6156
-2.500 0.0890 0.02964 0.01943 -0.0694 0.6247 0.6240
-2.250 0.1176 0.02943 0.01890 -0.0703 0.6205 0.6304
-2.000 0.1422 0.02942 0.01875 -0.0702 0.6148 0.6344
-1.750 0.1693 0.02934 0.01847 -0.0707 0.6104 0.6395
-1.500 0.1986 0.02922 0.01808 -0.0717 0.6069 0.6448
-1.250 0.2228 0.02933 0.01812 -0.0717 0.6019 0.6483
-1.000 0.2492 0.02939 0.01804 -0.0722 0.5976 0.6520
-0.750 0.2776 0.02941 0.01788 -0.0730 0.5942 0.6562
-0.500 0.3054 0.02951 0.01782 -0.0737 0.5908 0.6602
-0.250 0.3292 0.02980 0.01808 -0.0739 0.5862 0.6633
0.000 0.3555 0.02999 0.01818 -0.0743 0.5824 0.6669
0.250 0.3840 0.03013 0.01818 -0.0750 0.5793 0.6711
0.500 0.4105 0.03043 0.01840 -0.0756 0.5761 0.6752
0.750 0.4331 0.03096 0.01896 -0.0757 0.5722 0.6787
1.000 0.4582 0.03139 0.01936 -0.0761 0.5689 0.6828
1.250 0.4855 0.03176 0.01965 -0.0768 0.5662 0.6874
1.500 0.5126 0.03203 0.01987 -0.0771 0.5639 0.6916
1.750 0.5325 0.03286 0.02077 -0.0771 0.5598 0.6960
2.000 0.5547 0.03360 0.02153 -0.0775 0.5559 0.7008
2.250 0.5795 0.03410 0.02203 -0.0777 0.5528 0.7055
2.500 0.6054 0.03452 0.02246 -0.0779 0.5505 0.7107
2.750 0.6282 0.03532 0.02328 -0.0782 0.5478 0.7166
3.000 0.6400 0.03686 0.02498 -0.0778 0.5434 0.7218
3.250 0.6594 0.03784 0.02603 -0.0777 0.5398 0.7280
3.500 0.6839 0.03844 0.02668 -0.0779 0.5371 0.7345
3.750 0.7115 0.03875 0.02703 -0.0780 0.5349 0.7419
4.000 0.7095 0.04133 0.02980 -0.0770 0.5282 0.7493
4.250 0.7266 0.04238 0.03096 -0.0766 0.5243 0.7584
4.500 0.7507 0.04291 0.03161 -0.0765 0.5217 0.7689
4.750 0.7489 0.04546 0.03433 -0.0754 0.5160 0.7801
5.000 0.7514 0.04765 0.03670 -0.0746 0.5110 0.7941
5.250 0.7684 0.04869 0.03790 -0.0740 0.5083 0.8144
5.500 0.7898 0.04933 0.03876 -0.0735 0.5063 0.8525
5.750 0.7466 0.05509 0.04466 -0.0720 0.4967 1.0000
6.000 0.7706 0.05631 0.04588 -0.0728 0.4937 1.0000
6.250 0.8008 0.05702 0.04664 -0.0736 0.4918 1.0000
6.500 0.7652 0.06292 0.05254 -0.0734 0.4830 1.0000
6.750 0.7850 0.06441 0.05405 -0.0738 0.4798 1.0000
7.000 0.8159 0.06493 0.05461 -0.0741 0.4774 1.0000
7.250 0.7980 0.06897 0.05866 -0.0737 0.4675 1.0000
7.500 0.8239 0.06983 0.05957 -0.0738 0.4642 1.0000
7.750 0.8150 0.07348 0.06327 -0.0738 0.4573 1.0000
8.000 0.8242 0.07579 0.06564 -0.0740 0.4527 1.0000
8.250 0.8460 0.07710 0.06708 -0.0740 0.4497 1.0000
8.500 0.8378 0.08072 0.07075 -0.0741 0.4424 1.0000
8.750 0.8539 0.08231 0.07244 -0.0740 0.4373 1.0000
9.000 0.8815 0.08295 0.07319 -0.0738 0.4338 1.0000
9.250 0.8709 0.08660 0.07691 -0.0739 0.4241 1.0000
9.500 0.9007 0.08691 0.07736 -0.0735 0.4204 1.0000
9.750 0.8904 0.09062 0.08114 -0.0737 0.4104 1.0000
10.000 0.9141 0.09157 0.08229 -0.0735 0.4065 1.0000
10.500 0.9289 0.09617 0.08715 -0.0735 0.3924 1.0000
10.750 0.9266 0.09921 0.09030 -0.0738 0.3825 1.0000
11.000 0.9573 0.09883 0.09011 -0.0729 0.3772 1.0000
11.250 0.9540 0.10186 0.09326 -0.0732 0.3661 1.0000
11.750 0.9866 0.10359 0.09534 -0.0722 0.3497 1.0000
12.000 0.9864 0.10623 0.09818 -0.0724 0.3379 1.0000
12.250 0.9949 0.10747 0.09958 -0.0720 0.3259 1.0000
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Polar data table (+)
Polar graphs
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