K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: K3311 (smoothed) (k3311sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.73 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k3311sm-il-1000000-n5.txt Download as CSV file: xf-k3311sm-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: K3311 (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4341 0.14255 0.14076 -0.0194 1.0000 0.0050
-13.250 -0.4305 0.13878 0.13698 -0.0207 1.0000 0.0049
-12.250 -0.7548 0.04820 0.04639 -0.0685 1.0000 0.0056
-12.000 -0.7259 0.05061 0.04890 -0.0662 1.0000 0.0057
-11.750 -0.7008 0.05155 0.04988 -0.0668 1.0000 0.0057
-11.250 -0.8153 0.02601 0.02300 -0.0776 0.9902 0.0057
-11.000 -0.7913 0.02447 0.02129 -0.0788 0.9863 0.0058
-10.750 -0.7648 0.02310 0.01978 -0.0801 0.9835 0.0059
-10.500 -0.7440 0.02155 0.01802 -0.0803 0.9772 0.0060
-10.250 -0.7161 0.02041 0.01675 -0.0814 0.9733 0.0062
-10.000 -0.6863 0.01905 0.01519 -0.0831 0.9701 0.0063
-9.750 -0.6590 0.01793 0.01392 -0.0839 0.9636 0.0065
-9.500 -0.6274 0.01692 0.01275 -0.0854 0.9581 0.0068
-9.250 -0.5980 0.01596 0.01163 -0.0865 0.9502 0.0069
-9.000 -0.5673 0.01515 0.01066 -0.0876 0.9414 0.0071
-8.750 -0.5397 0.01445 0.00982 -0.0880 0.9295 0.0072
-8.500 -0.5132 0.01390 0.00914 -0.0880 0.9168 0.0073
-8.250 -0.4885 0.01330 0.00840 -0.0876 0.9029 0.0074
-8.000 -0.4653 0.01261 0.00756 -0.0870 0.8888 0.0077
-7.750 -0.4409 0.01220 0.00704 -0.0864 0.8750 0.0081
-7.500 -0.4163 0.01185 0.00659 -0.0859 0.8616 0.0083
-7.250 -0.3916 0.01153 0.00618 -0.0853 0.8483 0.0086
-7.000 -0.3668 0.01123 0.00578 -0.0848 0.8350 0.0089
-6.750 -0.3419 0.01094 0.00539 -0.0842 0.8217 0.0093
-6.500 -0.3170 0.01066 0.00501 -0.0836 0.8081 0.0097
-6.250 -0.2918 0.01042 0.00466 -0.0831 0.7950 0.0100
-6.000 -0.2668 0.01013 0.00429 -0.0826 0.7821 0.0107
-5.750 -0.2412 0.00992 0.00402 -0.0821 0.7692 0.0114
-5.500 -0.2153 0.00975 0.00379 -0.0817 0.7575 0.0122
-5.250 -0.1895 0.00957 0.00353 -0.0813 0.7456 0.0130
-5.000 -0.1634 0.00941 0.00330 -0.0809 0.7343 0.0136
-4.500 -0.1115 0.00902 0.00279 -0.0801 0.7118 0.0156
-4.250 -0.0851 0.00889 0.00260 -0.0798 0.7015 0.0167
-4.000 -0.0586 0.00878 0.00243 -0.0795 0.6914 0.0178
-3.750 -0.0321 0.00865 0.00224 -0.0792 0.6813 0.0191
-3.500 -0.0055 0.00851 0.00209 -0.0789 0.6718 0.0212
-3.250 0.0211 0.00842 0.00194 -0.0786 0.6626 0.0231
-3.000 0.0480 0.00833 0.00181 -0.0784 0.6530 0.0253
-2.750 0.0747 0.00822 0.00168 -0.0781 0.6443 0.0289
-2.500 0.1016 0.00816 0.00158 -0.0779 0.6353 0.0317
-2.250 0.1285 0.00805 0.00147 -0.0777 0.6264 0.0386
-2.000 0.1552 0.00798 0.00138 -0.0774 0.6180 0.0469
-1.750 0.1822 0.00789 0.00130 -0.0772 0.6093 0.0588
-1.500 0.2088 0.00778 0.00123 -0.0770 0.6014 0.0814
-1.250 0.2346 0.00755 0.00115 -0.0766 0.5925 0.1414
-1.000 0.2598 0.00723 0.00108 -0.0763 0.5845 0.2346
-0.500 0.3110 0.00681 0.00102 -0.0756 0.5672 0.3805
-0.250 0.3361 0.00660 0.00103 -0.0751 0.5587 0.4695
0.000 0.3616 0.00645 0.00106 -0.0747 0.5496 0.5415
0.250 0.3875 0.00638 0.00108 -0.0743 0.5416 0.5896
0.500 0.4141 0.00638 0.00110 -0.0740 0.5326 0.6135
0.750 0.4408 0.00638 0.00112 -0.0737 0.5241 0.6348
1.250 0.4935 0.00638 0.00120 -0.0730 0.5064 0.6862
1.750 0.5446 0.00636 0.00130 -0.0720 0.4888 0.7545
2.000 0.5694 0.00631 0.00136 -0.0713 0.4799 0.7987
2.250 0.5932 0.00625 0.00142 -0.0704 0.4705 0.8523
2.500 0.6385 0.00618 0.00154 -0.0742 0.4586 0.9469
2.750 0.6962 0.00630 0.00162 -0.0811 0.4458 0.9892
3.000 0.7274 0.00644 0.00171 -0.0819 0.4344 1.0000
3.250 0.7523 0.00656 0.00180 -0.0813 0.4243 1.0000
3.500 0.7770 0.00671 0.00189 -0.0807 0.4128 1.0000
3.750 0.8016 0.00686 0.00199 -0.0800 0.4006 1.0000
4.250 0.8503 0.00720 0.00224 -0.0787 0.3722 1.0000
4.500 0.8746 0.00739 0.00237 -0.0780 0.3580 1.0000
4.750 0.8988 0.00757 0.00251 -0.0774 0.3443 1.0000
5.000 0.9226 0.00779 0.00267 -0.0766 0.3285 1.0000
5.250 0.9464 0.00802 0.00285 -0.0759 0.3117 1.0000
5.500 0.9695 0.00829 0.00304 -0.0751 0.2918 1.0000
5.750 0.9910 0.00868 0.00329 -0.0740 0.2628 1.0000
6.000 1.0103 0.00923 0.00362 -0.0726 0.2215 1.0000
6.250 1.0309 0.00967 0.00393 -0.0714 0.1927 1.0000
6.500 1.0506 0.01019 0.00428 -0.0700 0.1615 1.0000
6.750 1.0705 0.01068 0.00463 -0.0687 0.1349 1.0000
7.000 1.0909 0.01112 0.00498 -0.0675 0.1141 1.0000
7.250 1.1100 0.01165 0.00539 -0.0661 0.0909 1.0000
7.500 1.1284 0.01221 0.00583 -0.0646 0.0688 1.0000
7.750 1.1470 0.01274 0.00627 -0.0632 0.0509 1.0000
8.000 1.1654 0.01327 0.00672 -0.0617 0.0377 1.0000
8.250 1.1843 0.01374 0.00716 -0.0602 0.0292 1.0000
8.500 1.2037 0.01416 0.00757 -0.0589 0.0243 1.0000
8.750 1.2226 0.01459 0.00799 -0.0575 0.0203 1.0000
9.000 1.2402 0.01506 0.00846 -0.0559 0.0168 1.0000
9.250 1.2585 0.01547 0.00889 -0.0544 0.0151 1.0000
9.500 1.2741 0.01590 0.00935 -0.0524 0.0134 1.0000
9.750 1.2879 0.01639 0.00986 -0.0501 0.0120 1.0000
10.000 1.3029 0.01684 0.01035 -0.0481 0.0113 1.0000
10.250 1.3174 0.01733 0.01086 -0.0461 0.0103 1.0000
10.500 1.3313 0.01787 0.01143 -0.0441 0.0097 1.0000
10.750 1.3437 0.01852 0.01211 -0.0419 0.0088 1.0000
11.000 1.3565 0.01916 0.01280 -0.0400 0.0083 1.0000
11.250 1.3698 0.01979 0.01350 -0.0382 0.0080 1.0000
11.500 1.3823 0.02051 0.01426 -0.0364 0.0077 1.0000
11.750 1.3941 0.02129 0.01509 -0.0346 0.0073 1.0000
12.000 1.4050 0.02216 0.01602 -0.0328 0.0070 1.0000
12.250 1.4152 0.02313 0.01703 -0.0312 0.0066 1.0000
12.500 1.4232 0.02430 0.01826 -0.0294 0.0061 1.0000
12.750 1.4324 0.02545 0.01948 -0.0280 0.0059 1.0000
13.000 1.4412 0.02668 0.02078 -0.0266 0.0058 1.0000
13.250 1.4511 0.02788 0.02206 -0.0255 0.0056 1.0000
13.500 1.4591 0.02930 0.02355 -0.0244 0.0054 1.0000
13.750 1.4663 0.03082 0.02515 -0.0234 0.0052 1.0000
14.000 1.4717 0.03258 0.02699 -0.0225 0.0051 1.0000
14.250 1.4771 0.03442 0.02891 -0.0217 0.0049 1.0000
14.500 1.4822 0.03632 0.03088 -0.0211 0.0047 1.0000
14.750 1.4854 0.03847 0.03310 -0.0205 0.0045 1.0000
15.000 1.4872 0.04084 0.03556 -0.0201 0.0045 1.0000
15.250 1.4874 0.04343 0.03824 -0.0197 0.0043 1.0000
15.500 1.4874 0.04613 0.04102 -0.0196 0.0041 1.0000
15.750 1.4840 0.04932 0.04432 -0.0195 0.0040 1.0000
16.000 1.4808 0.05255 0.04766 -0.0197 0.0040 1.0000
16.250 1.4771 0.05596 0.05117 -0.0200 0.0039 1.0000
16.500 1.4766 0.05904 0.05434 -0.0204 0.0039 1.0000
16.750 1.4711 0.06282 0.05823 -0.0210 0.0038 1.0000
17.000 1.4660 0.06664 0.06215 -0.0217 0.0038 1.0000
17.250 1.4603 0.07064 0.06626 -0.0225 0.0037 1.0000
17.500 1.4518 0.07513 0.07086 -0.0237 0.0037 1.0000
17.750 1.4443 0.07953 0.07536 -0.0249 0.0036 1.0000
18.000 1.4364 0.08410 0.08004 -0.0262 0.0036 1.0000
18.250 1.4266 0.08908 0.08512 -0.0278 0.0035 1.0000
18.500 1.4192 0.09374 0.08988 -0.0294 0.0034 1.0000
18.750 1.4054 0.09955 0.09580 -0.0315 0.0034 1.0000
19.000 1.3958 0.10479 0.10115 -0.0335 0.0033 1.0000
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Polar data table (+)
Polar graphs
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