SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il) Reynolds number: 100,000 Max Cl/Cd: 42.21 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s102s-il-100000-n5.txt Download as CSV file: xf-s102s-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SOMERS S102 AIRFOIL (SHARP)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4251 0.10071 0.09545 -0.0560 1.0000 0.0201
-11.500 -0.4273 0.09653 0.09131 -0.0574 1.0000 0.0199
-11.250 -0.4346 0.09078 0.08560 -0.0599 1.0000 0.0196
-11.000 -0.4473 0.08481 0.07963 -0.0628 1.0000 0.0193
-10.750 -0.4666 0.07891 0.07372 -0.0654 1.0000 0.0192
-10.500 -0.4871 0.07403 0.06881 -0.0668 1.0000 0.0189
-10.250 -0.5084 0.06997 0.06471 -0.0672 1.0000 0.0187
-10.000 -0.5314 0.06651 0.06121 -0.0664 1.0000 0.0186
-9.750 -0.5558 0.06378 0.05844 -0.0643 1.0000 0.0185
-9.500 -0.5832 0.06183 0.05647 -0.0607 1.0000 0.0183
-9.250 -0.5958 0.05849 0.05296 -0.0613 0.9926 0.0182
-9.000 -0.5908 0.05349 0.04757 -0.0648 0.9807 0.0179
-8.750 -0.5809 0.04905 0.04270 -0.0672 0.9705 0.0178
-8.250 -0.5529 0.04188 0.03470 -0.0689 0.9495 0.0178
-8.000 -0.5286 0.03871 0.03107 -0.0705 0.9435 0.0181
-7.750 -0.5090 0.03636 0.02836 -0.0703 0.9331 0.0188
-7.500 -0.4810 0.03382 0.02525 -0.0710 0.9271 0.0200
-7.250 -0.4569 0.03219 0.02357 -0.0713 0.9184 0.0210
-7.000 -0.4248 0.03044 0.02163 -0.0725 0.9138 0.0220
-6.750 -0.3993 0.02890 0.01992 -0.0721 0.9051 0.0227
-6.500 -0.3671 0.02734 0.01820 -0.0726 0.9003 0.0238
-6.250 -0.3404 0.02611 0.01687 -0.0723 0.8932 0.0249
-6.000 -0.3143 0.02502 0.01580 -0.0725 0.8868 0.0266
-5.750 -0.2872 0.02413 0.01480 -0.0727 0.8811 0.0303
-5.500 -0.2662 0.02327 0.01397 -0.0720 0.8732 0.0341
-5.250 -0.2402 0.02234 0.01299 -0.0722 0.8681 0.0393
-5.000 -0.2210 0.02164 0.01227 -0.0712 0.8598 0.0477
-4.750 -0.1972 0.02080 0.01142 -0.0710 0.8540 0.0649
-4.500 -0.1804 0.01960 0.01059 -0.0703 0.8471 0.1214
-4.250 -0.1777 0.01811 0.01130 -0.0670 0.8398 0.5407
-4.000 -0.1470 0.01916 0.01208 -0.0664 0.8361 0.6039
-3.750 -0.1255 0.02072 0.01362 -0.0628 0.8303 0.6360
-3.500 -0.1028 0.02214 0.01498 -0.0592 0.8254 0.6645
-3.250 -0.0746 0.02274 0.01548 -0.0573 0.8218 0.6727
-3.000 -0.0467 0.02241 0.01494 -0.0580 0.8175 0.6764
-2.750 -0.0223 0.02202 0.01436 -0.0587 0.8118 0.6806
-2.500 0.0053 0.02185 0.01405 -0.0589 0.8080 0.6821
-2.250 0.0348 0.02168 0.01373 -0.0595 0.8049 0.6838
-2.000 0.0617 0.02154 0.01349 -0.0597 0.8012 0.6855
-1.750 0.0856 0.02145 0.01330 -0.0596 0.7963 0.6874
-1.500 0.1131 0.02130 0.01304 -0.0600 0.7923 0.6895
-1.250 0.1429 0.02111 0.01274 -0.0609 0.7893 0.6913
-1.000 0.1731 0.02094 0.01245 -0.0620 0.7867 0.6932
-0.750 0.1961 0.02092 0.01238 -0.0621 0.7820 0.6956
-0.500 0.2224 0.02088 0.01228 -0.0624 0.7781 0.6972
-0.250 0.2505 0.02083 0.01218 -0.0628 0.7749 0.6982
0.000 0.2802 0.02076 0.01207 -0.0635 0.7723 0.6992
0.250 0.3062 0.02082 0.01211 -0.0636 0.7692 0.7006
0.500 0.3281 0.02098 0.01228 -0.0630 0.7646 0.7024
0.750 0.3544 0.02103 0.01234 -0.0632 0.7609 0.7041
1.000 0.3833 0.02105 0.01234 -0.0639 0.7581 0.7055
1.250 0.4141 0.02103 0.01231 -0.0648 0.7557 0.7069
1.500 0.4365 0.02123 0.01254 -0.0645 0.7509 0.7086
1.750 0.4622 0.02127 0.01258 -0.0646 0.7448 0.7102
2.000 0.4974 0.02086 0.01213 -0.0656 0.7366 0.7120
2.250 0.5272 0.02044 0.01168 -0.0653 0.7239 0.7135
2.500 0.5534 0.02008 0.01131 -0.0645 0.7091 0.7149
2.750 0.5791 0.01978 0.01102 -0.0637 0.6947 0.7164
3.000 0.6047 0.01957 0.01084 -0.0631 0.6815 0.7179
3.250 0.6322 0.01941 0.01069 -0.0629 0.6710 0.7195
3.500 0.6583 0.01930 0.01063 -0.0626 0.6603 0.7213
3.750 0.6817 0.01927 0.01069 -0.0619 0.6483 0.7231
4.000 0.7063 0.01920 0.01067 -0.0613 0.6350 0.7251
4.250 0.7299 0.01912 0.01065 -0.0606 0.6188 0.7273
4.500 0.7518 0.01905 0.01066 -0.0595 0.5989 0.7293
4.750 0.7702 0.01904 0.01074 -0.0577 0.5727 0.7313
5.000 0.7889 0.01902 0.01074 -0.0559 0.5294 0.7335
5.250 0.8062 0.01910 0.01022 -0.0534 0.4304 0.7358
5.500 0.8107 0.02005 0.01063 -0.0497 0.3499 0.7382
5.750 0.8176 0.02101 0.01125 -0.0468 0.2995 0.7407
6.000 0.8273 0.02181 0.01185 -0.0443 0.2669 0.7433
6.250 0.8385 0.02249 0.01243 -0.0420 0.2447 0.7456
6.500 0.8519 0.02313 0.01304 -0.0401 0.2291 0.7480
6.750 0.8673 0.02379 0.01367 -0.0386 0.2173 0.7507
7.000 0.8835 0.02449 0.01431 -0.0372 0.2073 0.7537
7.250 0.9024 0.02510 0.01494 -0.0363 0.1985 0.7572
7.500 0.9198 0.02583 0.01562 -0.0353 0.1912 0.7607
7.750 0.9393 0.02639 0.01628 -0.0344 0.1844 0.7640
8.000 0.9584 0.02705 0.01697 -0.0335 0.1789 0.7679
8.250 0.9789 0.02777 0.01769 -0.0329 0.1742 0.7721
8.500 1.0005 0.02841 0.01844 -0.0324 0.1689 0.7763
8.750 1.0203 0.02909 0.01918 -0.0317 0.1641 0.7803
9.000 1.0418 0.02987 0.01994 -0.0312 0.1599 0.7851
9.250 1.0643 0.03057 0.02081 -0.0309 0.1558 0.7906
9.500 1.0849 0.03128 0.02166 -0.0303 0.1517 0.7959
9.750 1.1055 0.03205 0.02249 -0.0298 0.1477 0.8025
10.000 1.1274 0.03289 0.02342 -0.0294 0.1441 0.8098
10.250 1.1463 0.03368 0.02446 -0.0286 0.1402 0.8186
10.500 1.1644 0.03448 0.02543 -0.0277 0.1364 0.8292
10.750 1.1820 0.03528 0.02632 -0.0268 0.1329 0.8426
11.000 1.1995 0.03616 0.02735 -0.0258 0.1296 0.8616
11.250 1.2105 0.03692 0.02849 -0.0238 0.1261 0.9021
11.500 1.2238 0.03781 0.02955 -0.0228 0.1223 1.0000
11.750 1.2407 0.03889 0.03066 -0.0224 0.1188 1.0000
12.000 1.2570 0.04016 0.03200 -0.0220 0.1155 1.0000
12.250 1.2664 0.04155 0.03368 -0.0209 0.1116 1.0000
12.500 1.2767 0.04288 0.03516 -0.0200 0.1079 1.0000
12.750 1.2875 0.04409 0.03641 -0.0192 0.1047 1.0000
13.000 1.2954 0.04569 0.03817 -0.0183 0.1015 1.0000
13.250 1.2993 0.04753 0.04030 -0.0172 0.0978 1.0000
13.500 1.3037 0.04919 0.04210 -0.0163 0.0943 1.0000
13.750 1.3095 0.05069 0.04363 -0.0156 0.0915 1.0000
14.000 1.3103 0.05297 0.04616 -0.0148 0.0883 1.0000
14.250 1.3091 0.05544 0.04890 -0.0141 0.0848 1.0000
14.500 1.3093 0.05762 0.05123 -0.0137 0.0817 1.0000
14.750 1.3109 0.05967 0.05330 -0.0135 0.0792 1.0000
15.000 1.3043 0.06313 0.05707 -0.0134 0.0761 1.0000
15.250 1.2980 0.06655 0.06075 -0.0136 0.0731 1.0000
15.500 1.2937 0.06969 0.06401 -0.0141 0.0705 1.0000
15.750 1.2913 0.07265 0.06700 -0.0147 0.0683 1.0000
16.000 1.2768 0.07787 0.07253 -0.0160 0.0660 1.0000
16.250 1.2615 0.08339 0.07832 -0.0178 0.0638 1.0000
16.500 1.2469 0.08908 0.08420 -0.0201 0.0620 1.0000
16.750 1.2341 0.09472 0.08997 -0.0228 0.0603 1.0000
17.000 1.2265 0.09963 0.09491 -0.0253 0.0586 1.0000
17.250 1.1978 0.10910 0.10463 -0.0305 0.0579 1.0000
17.500 1.1576 0.12179 0.11756 -0.0381 0.0579 1.0000
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Polar data table (+)
Polar graphs
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