SOMERS S102 AIRFOIL (BLUNT) (s102b-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SOMERS S102 AIRFOIL (BLUNT) (s102b-il) Reynolds number: 50,000 Max Cl/Cd: 31.11 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s102b-il-50000.txt Download as CSV file: xf-s102b-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SOMERS S102 AIRFOIL (BLUNT)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3384 0.10529 0.09872 -0.0209 1.0000 0.3937
-8.750 -0.3348 0.10177 0.09526 -0.0212 1.0000 0.3958
-8.500 -0.4404 0.07773 0.07230 -0.0423 1.0000 0.1732
-8.250 -0.4820 0.07491 0.06962 -0.0400 1.0000 0.1728
-8.000 -0.5193 0.07278 0.06760 -0.0369 1.0000 0.1732
-7.750 -0.5566 0.07048 0.06536 -0.0341 1.0000 0.1735
-7.500 -0.6558 0.07232 0.06652 -0.0364 1.0000 0.1865
-7.250 -0.6737 0.06661 0.06030 -0.0370 1.0000 0.1557
-7.000 -0.6702 0.06204 0.05531 -0.0364 1.0000 0.1347
-6.750 -0.6666 0.05790 0.05057 -0.0359 1.0000 0.1206
-6.500 -0.6580 0.05474 0.04637 -0.0354 1.0000 0.1085
-6.250 -0.6418 0.05080 0.04249 -0.0346 1.0000 0.1052
-6.000 -0.6247 0.04759 0.03891 -0.0341 1.0000 0.1011
-5.750 -0.6042 0.04475 0.03554 -0.0337 1.0000 0.0980
-5.500 -0.5826 0.04244 0.03284 -0.0332 1.0000 0.0982
-5.250 -0.5604 0.04043 0.03057 -0.0325 1.0000 0.1000
-5.000 -0.5375 0.03863 0.02850 -0.0317 1.0000 0.1018
-4.750 -0.5143 0.03705 0.02669 -0.0304 1.0000 0.1036
-4.500 -0.4916 0.03595 0.02533 -0.0287 1.0000 0.1080
-4.250 -0.4724 0.03475 0.02435 -0.0261 1.0000 0.1159
-4.000 -0.4533 0.03398 0.02354 -0.0232 1.0000 0.1249
-3.750 -0.4357 0.03298 0.02270 -0.0211 1.0000 0.1410
-3.500 -0.4146 0.03139 0.02144 -0.0207 1.0000 0.1729
-3.250 -0.2041 0.04127 0.03311 -0.0060 1.0000 0.9614
-3.000 -0.1873 0.04081 0.03243 -0.0065 1.0000 0.9678
-2.750 -0.1787 0.04047 0.03193 -0.0054 1.0000 0.9717
-2.500 -0.1625 0.04009 0.03137 -0.0058 1.0000 0.9752
-2.250 -0.1519 0.03981 0.03094 -0.0051 1.0000 0.9779
-2.000 -0.1437 0.03958 0.03059 -0.0039 1.0000 0.9800
-1.750 -0.1369 0.03938 0.03027 -0.0024 1.0000 0.9817
-1.500 -0.1295 0.03920 0.02999 -0.0010 1.0000 0.9834
-1.250 -0.1184 0.03902 0.02971 -0.0003 1.0000 0.9849
-1.000 -0.1077 0.03888 0.02947 0.0005 1.0000 0.9864
-0.750 -0.0981 0.03877 0.02927 0.0015 1.0000 0.9879
-0.500 -0.0880 0.03869 0.02912 0.0024 1.0000 0.9894
-0.250 -0.0783 0.03863 0.02899 0.0034 1.0000 0.9910
0.000 -0.0683 0.03861 0.02889 0.0043 1.0000 0.9926
0.250 -0.0562 0.03863 0.02886 0.0048 1.0000 0.9945
0.500 -0.0441 0.03866 0.02885 0.0053 1.0000 0.9962
0.750 -0.0313 0.03875 0.02889 0.0056 1.0000 0.9984
1.000 -0.0214 0.03881 0.02893 0.0065 1.0000 1.0000
1.250 -0.0181 0.03874 0.02884 0.0086 1.0000 1.0000
1.500 -0.0152 0.03867 0.02876 0.0107 1.0000 1.0000
1.750 -0.0124 0.03859 0.02867 0.0128 1.0000 1.0000
2.000 -0.0097 0.03850 0.02859 0.0148 1.0000 1.0000
2.250 -0.0070 0.03841 0.02851 0.0168 1.0000 1.0000
2.500 -0.0042 0.03833 0.02845 0.0187 1.0000 1.0000
2.750 -0.0003 0.03830 0.02844 0.0203 1.0000 1.0000
3.000 0.0073 0.03845 0.02861 0.0211 1.0000 1.0000
3.250 0.0195 0.03886 0.02905 0.0209 1.0000 1.0000
3.500 0.0355 0.03951 0.02973 0.0199 1.0000 1.0000
3.750 0.0542 0.04039 0.03064 0.0183 1.0000 1.0000
4.000 0.0744 0.04146 0.03177 0.0163 1.0000 1.0000
4.250 0.0956 0.04271 0.03308 0.0139 1.0000 1.0000
4.500 0.3192 0.04742 0.03789 -0.0157 0.8351 1.0000
4.750 0.3822 0.04758 0.03817 -0.0205 0.7994 1.0000
5.000 0.4311 0.04745 0.03819 -0.0231 0.7688 1.0000
5.250 0.4798 0.04701 0.03790 -0.0253 0.7401 1.0000
5.500 0.5413 0.04574 0.03683 -0.0279 0.7135 1.0000
5.750 0.5981 0.04381 0.03516 -0.0292 0.6858 1.0000
6.000 0.6515 0.04121 0.03283 -0.0293 0.6559 1.0000
6.250 0.7232 0.03629 0.02821 -0.0289 0.6231 1.0000
6.500 0.7757 0.03169 0.02382 -0.0265 0.5687 1.0000
6.750 0.8287 0.02774 0.01945 -0.0245 0.4809 1.0000
7.000 0.8660 0.02784 0.01873 -0.0245 0.4178 1.0000
7.250 0.8992 0.02910 0.01960 -0.0256 0.3809 1.0000
7.500 0.9365 0.03048 0.02074 -0.0277 0.3548 1.0000
7.750 0.9734 0.03198 0.02222 -0.0299 0.3362 1.0000
8.000 1.0097 0.03360 0.02384 -0.0321 0.3210 1.0000
8.250 1.0448 0.03531 0.02558 -0.0343 0.3077 1.0000
8.500 1.0801 0.03717 0.02748 -0.0364 0.2969 1.0000
8.750 1.1053 0.03926 0.02989 -0.0375 0.2882 1.0000
9.000 1.1388 0.04139 0.03205 -0.0394 0.2788 1.0000
9.250 1.1566 0.04377 0.03486 -0.0396 0.2716 1.0000
9.500 1.1899 0.04625 0.03731 -0.0414 0.2639 1.0000
9.750 1.1947 0.04910 0.04072 -0.0402 0.2584 1.0000
10.000 1.2153 0.05171 0.04351 -0.0405 0.2514 1.0000
10.250 1.2275 0.05502 0.04710 -0.0402 0.2466 1.0000
10.500 1.2177 0.05880 0.05135 -0.0379 0.2432 1.0000
10.750 1.2086 0.06266 0.05553 -0.0359 0.2395 1.0000
11.000 1.2400 0.06559 0.05843 -0.0370 0.2324 1.0000
11.250 1.2104 0.07049 0.06369 -0.0340 0.2318 1.0000
11.500 1.1745 0.07583 0.06926 -0.0312 0.2320 1.0000
11.750 1.1361 0.08232 0.07590 -0.0300 0.2328 1.0000
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Polar data table (+)
Polar graphs
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