K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: K3311 (smoothed) (k3311sm-il) Reynolds number: 100,000 Max Cl/Cd: 55.35 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k3311sm-il-100000.txt Download as CSV file: xf-k3311sm-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3545 0.10629 0.10129 -0.0362 1.0000 0.0917
-9.250 -0.3686 0.10414 0.09926 -0.0397 1.0000 0.0934
-9.000 -0.3886 0.10209 0.09736 -0.0433 1.0000 0.0940
-8.750 -0.3514 0.09685 0.09204 -0.0370 1.0000 0.0993
-8.500 -0.3518 0.09420 0.08945 -0.0371 1.0000 0.1035
-8.250 -0.2824 0.08257 0.07830 -0.0368 1.0000 0.1144
-8.000 -0.2899 0.08003 0.07584 -0.0360 1.0000 0.1184
-7.750 -0.3156 0.07816 0.07412 -0.0355 1.0000 0.1213
-7.500 -0.3821 0.08382 0.07948 -0.0349 1.0000 0.1143
-7.250 -0.3966 0.08204 0.07782 -0.0328 1.0000 0.1165
-7.000 -0.4161 0.07985 0.07575 -0.0325 1.0000 0.1195
-6.750 -0.4506 0.07725 0.07317 -0.0363 1.0000 0.1221
-6.500 -0.4638 0.07380 0.06974 -0.0358 1.0000 0.1240
-6.250 -0.4557 0.07224 0.06831 -0.0299 1.0000 0.1271
-6.000 -0.4604 0.07020 0.06630 -0.0283 1.0000 0.1319
-5.750 -0.4734 0.06624 0.06221 -0.0318 1.0000 0.1392
-5.500 -0.4594 0.06415 0.06018 -0.0298 0.9980 0.1450
-5.250 -0.4276 0.05864 0.05438 -0.0397 0.9888 0.1682
-5.000 -0.3958 0.05530 0.05104 -0.0424 0.9823 0.1850
-4.750 -0.3667 0.05224 0.04789 -0.0458 0.9736 0.2135
-4.500 -0.3108 0.03746 0.03079 -0.0573 0.9664 0.0956
-4.250 -0.2699 0.03348 0.02597 -0.0590 0.9596 0.0793
-4.000 -0.2342 0.03016 0.02228 -0.0608 0.9529 0.0767
-3.750 -0.1956 0.02814 0.01972 -0.0626 0.9454 0.0782
-3.500 -0.1578 0.02643 0.01756 -0.0641 0.9380 0.0807
-3.250 -0.1194 0.02446 0.01553 -0.0660 0.9311 0.0842
-3.000 -0.0817 0.02349 0.01439 -0.0676 0.9233 0.0932
-2.750 -0.0436 0.02206 0.01307 -0.0694 0.9162 0.1019
-2.500 -0.0097 0.02112 0.01221 -0.0704 0.9079 0.1182
-2.250 0.0284 0.01991 0.01123 -0.0722 0.9010 0.1569
-2.000 0.0452 0.01767 0.01118 -0.0698 0.8923 0.6287
-1.750 0.0791 0.01712 0.01105 -0.0690 0.8863 0.7864
-1.500 0.2022 0.01665 0.01062 -0.0845 0.8903 0.9841
-1.250 0.2610 0.01624 0.00991 -0.0913 0.8849 1.0000
-1.000 0.2829 0.01617 0.00963 -0.0910 0.8721 1.0000
-0.750 0.3091 0.01617 0.00942 -0.0910 0.8607 1.0000
-0.500 0.3436 0.01605 0.00911 -0.0922 0.8522 1.0000
-0.250 0.3719 0.01604 0.00895 -0.0922 0.8417 1.0000
0.000 0.3958 0.01616 0.00893 -0.0914 0.8301 1.0000
0.250 0.4235 0.01621 0.00885 -0.0912 0.8201 1.0000
0.500 0.4546 0.01616 0.00867 -0.0914 0.8114 1.0000
0.750 0.4773 0.01635 0.00877 -0.0904 0.7996 1.0000
1.000 0.5023 0.01650 0.00884 -0.0897 0.7891 1.0000
1.250 0.5340 0.01644 0.00866 -0.0898 0.7811 1.0000
1.500 0.5560 0.01668 0.00886 -0.0887 0.7692 1.0000
1.750 0.5799 0.01690 0.00902 -0.0878 0.7581 1.0000
2.000 0.6073 0.01700 0.00905 -0.0874 0.7487 1.0000
2.250 0.6339 0.01712 0.00911 -0.0868 0.7385 1.0000
2.500 0.6569 0.01739 0.00938 -0.0858 0.7271 1.0000
2.750 0.6821 0.01759 0.00955 -0.0851 0.7166 1.0000
3.000 0.7117 0.01762 0.00952 -0.0849 0.7078 1.0000
3.250 0.7340 0.01793 0.00984 -0.0838 0.6958 1.0000
3.500 0.7578 0.01820 0.01014 -0.0829 0.6844 1.0000
3.750 0.7838 0.01839 0.01032 -0.0823 0.6739 1.0000
4.000 0.8121 0.01848 0.01037 -0.0819 0.6640 1.0000
4.250 0.8348 0.01877 0.01074 -0.0808 0.6516 1.0000
4.500 0.8584 0.01905 0.01105 -0.0799 0.6395 1.0000
4.750 0.8832 0.01927 0.01130 -0.0791 0.6278 1.0000
5.000 0.9094 0.01943 0.01147 -0.0784 0.6162 1.0000
5.250 0.9370 0.01953 0.01159 -0.0779 0.6048 1.0000
5.500 0.9602 0.01978 0.01190 -0.0768 0.5914 1.0000
5.750 0.9836 0.02001 0.01220 -0.0758 0.5778 1.0000
6.000 1.0075 0.02022 0.01246 -0.0748 0.5639 1.0000
6.250 1.0314 0.02040 0.01273 -0.0737 0.5495 1.0000
6.500 1.0553 0.02056 0.01294 -0.0727 0.5345 1.0000
6.750 1.0792 0.02071 0.01314 -0.0716 0.5190 1.0000
7.000 1.1034 0.02085 0.01330 -0.0705 0.5029 1.0000
7.250 1.1237 0.02109 0.01366 -0.0689 0.4847 1.0000
7.500 1.1438 0.02125 0.01391 -0.0672 0.4650 1.0000
7.750 1.1647 0.02127 0.01390 -0.0655 0.4434 1.0000
8.000 1.1801 0.02138 0.01406 -0.0631 0.4178 1.0000
8.250 1.1939 0.02157 0.01429 -0.0604 0.3907 1.0000
8.500 1.2065 0.02190 0.01467 -0.0577 0.3627 1.0000
8.750 1.2171 0.02237 0.01513 -0.0548 0.3328 1.0000
9.000 1.2247 0.02303 0.01572 -0.0515 0.3007 1.0000
9.250 1.2282 0.02391 0.01655 -0.0479 0.2633 1.0000
9.500 1.2249 0.02514 0.01759 -0.0434 0.2207 1.0000
9.750 1.2132 0.02690 0.01903 -0.0381 0.1759 1.0000
10.000 1.1986 0.02928 0.02103 -0.0332 0.1358 1.0000
10.250 1.1879 0.03178 0.02328 -0.0293 0.1106 1.0000
10.500 1.1815 0.03422 0.02555 -0.0262 0.0955 1.0000
10.750 1.1800 0.03651 0.02781 -0.0238 0.0838 1.0000
11.000 1.1832 0.03871 0.03001 -0.0217 0.0752 1.0000
11.250 1.1932 0.04090 0.03204 -0.0200 0.0687 1.0000
11.500 1.2042 0.04281 0.03411 -0.0185 0.0630 1.0000
11.750 1.2266 0.04509 0.03624 -0.0177 0.0573 1.0000
12.000 1.2443 0.04729 0.03871 -0.0165 0.0544 1.0000
12.250 1.2637 0.04981 0.04145 -0.0157 0.0519 1.0000
12.500 1.2787 0.05241 0.04418 -0.0148 0.0493 1.0000
12.750 1.2988 0.05675 0.04865 -0.0147 0.0468 1.0000
13.000 1.2915 0.05952 0.05176 -0.0127 0.0461 1.0000
13.250 1.2836 0.06291 0.05549 -0.0111 0.0457 1.0000
13.500 1.2738 0.06669 0.05958 -0.0099 0.0455 1.0000
13.750 1.2608 0.07083 0.06403 -0.0092 0.0454 1.0000
14.000 1.2458 0.07527 0.06875 -0.0089 0.0454 1.0000
14.250 1.2275 0.08019 0.07394 -0.0093 0.0455 1.0000
14.500 1.2076 0.08555 0.07955 -0.0104 0.0457 1.0000
14.750 1.1865 0.09140 0.08561 -0.0122 0.0459 1.0000
15.000 1.1661 0.09759 0.09201 -0.0145 0.0462 1.0000
15.250 1.1432 0.10445 0.09905 -0.0177 0.0465 1.0000
15.500 1.1223 0.11175 0.10650 -0.0212 0.0468 1.0000
15.750 1.1024 0.11933 0.11424 -0.0252 0.0472 1.0000
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