S4110 (s4110-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4110 (s4110-il) Reynolds number: 500,000 Max Cl/Cd: 89.88 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4110-il-500000-n5.txt Download as CSV file: xf-s4110-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4110
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4373 0.08372 0.08138 -0.0337 1.0000 0.0090
-9.000 -0.4444 0.07941 0.07711 -0.0351 1.0000 0.0091
-8.500 -0.5470 0.03214 0.02919 -0.0765 0.9882 0.0084
-8.250 -0.5232 0.02564 0.02194 -0.0823 0.9841 0.0085
-8.000 -0.4984 0.02263 0.01848 -0.0842 0.9795 0.0086
-7.750 -0.4705 0.02042 0.01591 -0.0858 0.9755 0.0087
-7.500 -0.4400 0.01873 0.01392 -0.0873 0.9727 0.0088
-7.250 -0.4084 0.01738 0.01232 -0.0889 0.9705 0.0089
-7.000 -0.3837 0.01563 0.01030 -0.0890 0.9640 0.0092
-6.750 -0.3539 0.01458 0.00911 -0.0899 0.9599 0.0095
-6.500 -0.3221 0.01378 0.00819 -0.0910 0.9567 0.0099
-6.250 -0.2949 0.01313 0.00744 -0.0910 0.9499 0.0102
-6.000 -0.2643 0.01251 0.00672 -0.0917 0.9451 0.0106
-5.750 -0.2347 0.01196 0.00608 -0.0922 0.9395 0.0111
-5.500 -0.2055 0.01146 0.00547 -0.0925 0.9329 0.0115
-5.250 -0.1757 0.01101 0.00493 -0.0929 0.9269 0.0120
-5.000 -0.1475 0.01061 0.00446 -0.0929 0.9191 0.0127
-4.750 -0.1189 0.01018 0.00397 -0.0930 0.9119 0.0141
-4.500 -0.0910 0.00986 0.00358 -0.0929 0.9035 0.0153
-4.250 -0.0630 0.00957 0.00322 -0.0928 0.8955 0.0171
-4.000 -0.0353 0.00926 0.00290 -0.0927 0.8871 0.0228
-3.750 -0.0078 0.00900 0.00268 -0.0925 0.8788 0.0339
-3.250 0.0474 0.00870 0.00232 -0.0922 0.8618 0.0493
-3.000 0.0750 0.00854 0.00217 -0.0920 0.8534 0.0595
-2.750 0.1025 0.00841 0.00203 -0.0919 0.8442 0.0688
-2.500 0.1300 0.00827 0.00189 -0.0917 0.8351 0.0804
-2.250 0.1575 0.00815 0.00176 -0.0915 0.8258 0.0938
-2.000 0.1850 0.00803 0.00165 -0.0913 0.8158 0.1085
-1.750 0.2124 0.00791 0.00155 -0.0911 0.8057 0.1296
-1.500 0.2397 0.00778 0.00147 -0.0909 0.7950 0.1597
-1.000 0.2941 0.00749 0.00134 -0.0905 0.7711 0.2430
-0.750 0.3211 0.00730 0.00130 -0.0904 0.7589 0.3091
-0.500 0.3480 0.00711 0.00128 -0.0902 0.7457 0.3817
-0.250 0.3747 0.00694 0.00128 -0.0899 0.7307 0.4607
0.000 0.4012 0.00681 0.00129 -0.0896 0.7149 0.5324
0.250 0.4273 0.00665 0.00132 -0.0892 0.6988 0.6142
0.500 0.4526 0.00651 0.00136 -0.0885 0.6819 0.6991
0.750 0.4766 0.00636 0.00142 -0.0874 0.6634 0.7865
1.000 0.4969 0.00621 0.00147 -0.0853 0.6435 0.8870
1.250 0.5317 0.00621 0.00144 -0.0865 0.6193 1.0000
1.500 0.5577 0.00638 0.00149 -0.0861 0.5943 1.0000
2.000 0.6091 0.00681 0.00162 -0.0851 0.5344 1.0000
2.250 0.6345 0.00706 0.00172 -0.0845 0.5015 1.0000
2.500 0.6597 0.00734 0.00184 -0.0840 0.4673 1.0000
2.750 0.6851 0.00763 0.00197 -0.0835 0.4353 1.0000
3.000 0.7105 0.00792 0.00212 -0.0831 0.4035 1.0000
3.250 0.7355 0.00825 0.00228 -0.0826 0.3686 1.0000
3.500 0.7608 0.00856 0.00247 -0.0821 0.3391 1.0000
3.750 0.7859 0.00889 0.00266 -0.0816 0.3092 1.0000
4.000 0.8109 0.00923 0.00287 -0.0812 0.2798 1.0000
4.250 0.8362 0.00956 0.00309 -0.0807 0.2553 1.0000
4.500 0.8611 0.00991 0.00333 -0.0803 0.2302 1.0000
4.750 0.8861 0.01025 0.00357 -0.0798 0.2081 1.0000
5.000 0.9111 0.01059 0.00383 -0.0793 0.1877 1.0000
5.250 0.9358 0.01095 0.00410 -0.0789 0.1675 1.0000
5.500 0.9604 0.01132 0.00440 -0.0784 0.1501 1.0000
5.750 0.9851 0.01168 0.00469 -0.0779 0.1356 1.0000
6.250 1.0344 0.01238 0.00531 -0.0769 0.1113 1.0000
6.500 1.0590 0.01272 0.00565 -0.0763 0.1022 1.0000
6.750 1.0832 0.01310 0.00600 -0.0758 0.0925 1.0000
7.000 1.1071 0.01349 0.00637 -0.0752 0.0838 1.0000
7.250 1.1312 0.01386 0.00674 -0.0746 0.0759 1.0000
7.500 1.1547 0.01428 0.00716 -0.0740 0.0680 1.0000
7.750 1.1780 0.01471 0.00758 -0.0733 0.0608 1.0000
8.000 1.2011 0.01515 0.00802 -0.0726 0.0544 1.0000
8.250 1.2233 0.01567 0.00851 -0.0718 0.0471 1.0000
8.500 1.2457 0.01614 0.00899 -0.0710 0.0416 1.0000
8.750 1.2674 0.01668 0.00954 -0.0701 0.0365 1.0000
9.000 1.2891 0.01718 0.01008 -0.0693 0.0327 1.0000
9.250 1.3097 0.01780 0.01070 -0.0682 0.0289 1.0000
9.500 1.3310 0.01830 0.01126 -0.0673 0.0268 1.0000
9.750 1.3512 0.01888 0.01189 -0.0663 0.0242 1.0000
10.000 1.3699 0.01959 0.01261 -0.0650 0.0214 1.0000
10.250 1.3896 0.02014 0.01326 -0.0639 0.0197 1.0000
10.500 1.4078 0.02081 0.01397 -0.0626 0.0177 1.0000
10.750 1.4240 0.02162 0.01482 -0.0610 0.0158 1.0000
11.000 1.4406 0.02229 0.01558 -0.0595 0.0149 1.0000
11.250 1.4547 0.02302 0.01638 -0.0575 0.0137 1.0000
11.500 1.4670 0.02383 0.01726 -0.0554 0.0127 1.0000
11.750 1.4768 0.02482 0.01831 -0.0530 0.0116 1.0000
12.000 1.4874 0.02574 0.01934 -0.0508 0.0110 1.0000
12.250 1.4976 0.02670 0.02040 -0.0487 0.0104 1.0000
12.500 1.5069 0.02775 0.02155 -0.0467 0.0097 1.0000
12.750 1.5147 0.02894 0.02283 -0.0447 0.0092 1.0000
13.000 1.5206 0.03032 0.02430 -0.0426 0.0087 1.0000
13.250 1.5236 0.03200 0.02609 -0.0406 0.0083 1.0000
13.500 1.5265 0.03376 0.02796 -0.0388 0.0080 1.0000
13.750 1.5304 0.03551 0.02984 -0.0372 0.0078 1.0000
14.000 1.5330 0.03746 0.03193 -0.0359 0.0075 1.0000
14.250 1.5350 0.03958 0.03418 -0.0348 0.0073 1.0000
14.500 1.5345 0.04206 0.03679 -0.0339 0.0070 1.0000
14.750 1.5341 0.04466 0.03954 -0.0334 0.0068 1.0000
15.000 1.5323 0.04758 0.04259 -0.0331 0.0066 1.0000
15.250 1.5272 0.05106 0.04621 -0.0333 0.0064 1.0000
15.500 1.5217 0.05482 0.05010 -0.0338 0.0063 1.0000
15.750 1.5127 0.05932 0.05475 -0.0350 0.0062 1.0000
16.000 1.5020 0.06436 0.05993 -0.0367 0.0060 1.0000
16.250 1.4886 0.07021 0.06596 -0.0391 0.0060 1.0000
16.500 1.4727 0.07688 0.07279 -0.0422 0.0059 1.0000
16.750 1.4549 0.08431 0.08039 -0.0460 0.0058 1.0000
17.000 1.4351 0.09253 0.08879 -0.0504 0.0058 1.0000
17.250 1.4137 0.10139 0.09782 -0.0553 0.0058 1.0000
17.500 1.3923 0.11054 0.10713 -0.0604 0.0059 1.0000
17.750 1.3694 0.12023 0.11698 -0.0660 0.0059 1.0000
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