S1012 (s1012-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1012 (s1012-il) Reynolds number: 100,000 Max Cl/Cd: 37.24 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1012-il-100000.txt Download as CSV file: xf-s1012-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S1012
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5135 0.11541 0.11043 -0.0203 1.0000 0.1712
-11.500 -0.8515 0.06949 0.06368 -0.0439 1.0000 0.0846
-11.250 -0.8677 0.06507 0.05914 -0.0423 1.0000 0.0843
-11.000 -0.8873 0.06121 0.05510 -0.0394 1.0000 0.0841
-10.750 -0.9034 0.05732 0.05094 -0.0366 1.0000 0.0841
-10.500 -0.9195 0.05391 0.04715 -0.0330 1.0000 0.0845
-10.250 -0.9169 0.05008 0.04325 -0.0315 1.0000 0.0864
-10.000 -0.8938 0.04917 0.04251 -0.0313 1.0000 0.0903
-9.750 -0.8971 0.04648 0.03956 -0.0282 1.0000 0.0921
-9.500 -0.9027 0.04385 0.03660 -0.0242 1.0000 0.0935
-9.250 -0.9106 0.04173 0.03413 -0.0193 1.0000 0.0952
-9.000 -0.9192 0.04010 0.03207 -0.0139 1.0000 0.0971
-8.750 -0.9178 0.03792 0.02973 -0.0103 1.0000 0.0997
-8.500 -0.9074 0.03669 0.02852 -0.0079 1.0000 0.1030
-8.250 -0.9000 0.03531 0.02693 -0.0049 1.0000 0.1064
-8.000 -0.8945 0.03391 0.02512 -0.0013 1.0000 0.1104
-7.750 -0.8822 0.03213 0.02321 0.0008 1.0000 0.1144
-7.500 -0.8675 0.03102 0.02205 0.0028 1.0000 0.1190
-7.250 -0.8546 0.02996 0.02068 0.0052 1.0000 0.1246
-7.000 -0.8373 0.02855 0.01923 0.0067 1.0000 0.1299
-6.750 -0.8203 0.02760 0.01817 0.0084 1.0000 0.1360
-6.500 -0.8027 0.02650 0.01691 0.0101 1.0000 0.1430
-6.250 -0.7841 0.02564 0.01608 0.0114 1.0000 0.1504
-6.000 -0.7647 0.02468 0.01502 0.0128 1.0000 0.1585
-5.750 -0.7458 0.02396 0.01429 0.0142 1.0000 0.1681
-5.500 -0.7261 0.02309 0.01348 0.0154 1.0000 0.1781
-5.250 -0.7069 0.02234 0.01272 0.0168 1.0000 0.1899
-5.000 -0.6881 0.02165 0.01207 0.0183 1.0000 0.2039
-4.750 -0.6696 0.02093 0.01145 0.0197 1.0000 0.2200
-4.500 -0.6519 0.02020 0.01090 0.0213 1.0000 0.2397
-4.250 -0.6346 0.01949 0.01036 0.0229 1.0000 0.2662
-4.000 -0.6190 0.01865 0.00986 0.0248 1.0000 0.3027
-3.750 -0.6060 0.01761 0.00938 0.0272 1.0000 0.3704
-3.500 -0.6016 0.01615 0.00921 0.0317 1.0000 0.5471
-3.250 -0.5933 0.01691 0.01077 0.0384 1.0000 0.7416
-3.000 -0.5822 0.01758 0.01137 0.0431 1.0000 0.7939
-2.750 -0.5687 0.01830 0.01202 0.0475 1.0000 0.8274
-2.500 -0.5511 0.01902 0.01267 0.0512 1.0000 0.8544
-2.250 -0.5331 0.01960 0.01315 0.0545 1.0000 0.8794
-2.000 -0.4836 0.02079 0.01421 0.0523 1.0000 0.9005
-1.750 -0.4051 0.02217 0.01540 0.0441 1.0000 0.9191
-1.500 -0.3173 0.02321 0.01627 0.0336 1.0000 0.9355
-1.250 -0.2440 0.02379 0.01673 0.0251 1.0000 0.9521
-1.000 -0.1674 0.02419 0.01704 0.0157 1.0000 0.9706
-0.750 -0.0632 0.02424 0.01701 0.0006 1.0000 0.9916
-0.500 -0.0142 0.02414 0.01688 -0.0048 1.0000 1.0000
-0.250 -0.0071 0.02411 0.01683 -0.0024 1.0000 1.0000
0.000 0.0000 0.02409 0.01682 0.0000 1.0000 1.0000
0.250 0.0072 0.02410 0.01683 0.0024 1.0000 1.0000
0.500 0.0142 0.02414 0.01688 0.0048 1.0000 1.0000
0.750 0.0650 0.02423 0.01700 -0.0009 0.9911 1.0000
1.000 0.1680 0.02419 0.01704 -0.0158 0.9705 1.0000
1.250 0.2452 0.02376 0.01670 -0.0253 0.9516 1.0000
1.500 0.3172 0.02321 0.01627 -0.0335 0.9356 1.0000
1.750 0.4040 0.02219 0.01542 -0.0440 0.9193 1.0000
2.000 0.4843 0.02076 0.01418 -0.0524 0.9003 1.0000
2.250 0.5329 0.01959 0.01314 -0.0544 0.8793 1.0000
2.500 0.5510 0.01904 0.01268 -0.0512 0.8547 1.0000
2.750 0.5687 0.01829 0.01201 -0.0475 0.8274 1.0000
3.000 0.5822 0.01759 0.01138 -0.0431 0.7942 1.0000
3.250 0.5933 0.01692 0.01077 -0.0385 0.7420 1.0000
3.500 0.6015 0.01615 0.00920 -0.0317 0.5472 1.0000
3.750 0.6060 0.01760 0.00937 -0.0272 0.3712 1.0000
4.000 0.6189 0.01864 0.00986 -0.0248 0.3029 1.0000
4.250 0.6346 0.01948 0.01035 -0.0229 0.2663 1.0000
4.500 0.6519 0.02020 0.01090 -0.0212 0.2396 1.0000
4.750 0.6695 0.02092 0.01144 -0.0197 0.2200 1.0000
5.000 0.6881 0.02166 0.01207 -0.0182 0.2039 1.0000
5.250 0.7068 0.02234 0.01272 -0.0168 0.1898 1.0000
5.500 0.7260 0.02309 0.01348 -0.0154 0.1779 1.0000
5.750 0.7458 0.02396 0.01428 -0.0142 0.1682 1.0000
6.000 0.7647 0.02468 0.01502 -0.0128 0.1585 1.0000
6.250 0.7840 0.02564 0.01608 -0.0114 0.1504 1.0000
6.500 0.8027 0.02650 0.01691 -0.0100 0.1430 1.0000
6.750 0.8203 0.02760 0.01818 -0.0084 0.1361 1.0000
7.000 0.8373 0.02854 0.01921 -0.0067 0.1299 1.0000
7.250 0.8545 0.02996 0.02069 -0.0052 0.1245 1.0000
7.500 0.8675 0.03102 0.02205 -0.0028 0.1190 1.0000
7.750 0.8822 0.03214 0.02322 -0.0008 0.1145 1.0000
8.000 0.8944 0.03391 0.02512 0.0013 0.1103 1.0000
8.250 0.8999 0.03529 0.02691 0.0049 0.1065 1.0000
8.500 0.9074 0.03668 0.02851 0.0079 0.1029 1.0000
8.750 0.9178 0.03790 0.02971 0.0103 0.0996 1.0000
9.000 0.9190 0.04006 0.03204 0.0139 0.0970 1.0000
9.250 0.9104 0.04172 0.03412 0.0193 0.0951 1.0000
9.500 0.9027 0.04384 0.03658 0.0242 0.0935 1.0000
9.750 0.8972 0.04646 0.03953 0.0282 0.0920 1.0000
10.000 0.8934 0.04925 0.04260 0.0313 0.0904 1.0000
10.250 0.9164 0.05012 0.04331 0.0316 0.0865 1.0000
10.500 0.9190 0.05383 0.04708 0.0331 0.0845 1.0000
10.750 0.9036 0.05735 0.05097 0.0365 0.0841 1.0000
11.000 0.8874 0.06124 0.05513 0.0394 0.0842 1.0000
11.250 0.8696 0.06514 0.05920 0.0421 0.0844 1.0000
11.500 0.8522 0.06956 0.06374 0.0438 0.0846 1.0000
11.750 0.7072 0.08611 0.08079 0.0377 0.0965 1.0000
12.000 0.7012 0.09220 0.08689 0.0356 0.0973 1.0000
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Polar data table (+)
Polar graphs
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