SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il) Reynolds number: 50,000 Max Cl/Cd: 30.2 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s102s-il-50000.txt Download as CSV file: xf-s102s-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3217 0.10690 0.10029 -0.0256 1.0000 0.3821
-9.000 -0.3272 0.10443 0.09793 -0.0245 1.0000 0.3906
-8.750 -0.3308 0.10145 0.09504 -0.0239 1.0000 0.3910
-8.500 -0.4895 0.08347 0.07756 -0.0443 1.0000 0.1905
-8.250 -0.5341 0.08091 0.07518 -0.0417 1.0000 0.1881
-8.000 -0.5748 0.07921 0.07362 -0.0380 1.0000 0.1886
-7.750 -0.6129 0.07693 0.07140 -0.0351 1.0000 0.1875
-7.500 -0.6532 0.07372 0.06806 -0.0334 1.0000 0.1783
-7.250 -0.6742 0.06905 0.06314 -0.0326 1.0000 0.1593
-7.000 -0.6879 0.06448 0.05814 -0.0319 1.0000 0.1415
-6.750 -0.6899 0.06011 0.05324 -0.0310 1.0000 0.1258
-6.500 -0.6837 0.05649 0.04911 -0.0299 1.0000 0.1150
-6.250 -0.6747 0.05334 0.04502 -0.0288 1.0000 0.1046
-6.000 -0.6598 0.05002 0.04156 -0.0279 1.0000 0.1020
-5.750 -0.6439 0.04722 0.03837 -0.0270 1.0000 0.1006
-5.500 -0.6260 0.04474 0.03550 -0.0261 1.0000 0.1003
-5.250 -0.6062 0.04250 0.03291 -0.0251 1.0000 0.1001
-5.000 -0.5852 0.04047 0.03056 -0.0239 1.0000 0.1003
-4.750 -0.5636 0.03867 0.02848 -0.0226 1.0000 0.1005
-4.500 -0.5420 0.03724 0.02679 -0.0211 1.0000 0.1030
-4.250 -0.5214 0.03587 0.02539 -0.0191 1.0000 0.1084
-4.000 -0.5022 0.03496 0.02455 -0.0166 1.0000 0.1154
-3.750 -0.4848 0.03416 0.02378 -0.0136 1.0000 0.1236
-3.500 -0.4695 0.03321 0.02294 -0.0111 1.0000 0.1388
-3.250 -0.1972 0.04361 0.03550 -0.0070 1.0000 0.9630
-3.000 -0.1832 0.04323 0.03492 -0.0070 1.0000 0.9692
-2.750 -0.1677 0.04281 0.03432 -0.0073 1.0000 0.9737
-2.500 -0.1548 0.04248 0.03381 -0.0071 1.0000 0.9769
-2.250 -0.1454 0.04223 0.03342 -0.0061 1.0000 0.9794
-2.000 -0.1383 0.04202 0.03310 -0.0048 1.0000 0.9810
-1.750 -0.1318 0.04184 0.03281 -0.0032 1.0000 0.9824
-1.500 -0.1225 0.04165 0.03250 -0.0022 1.0000 0.9840
-1.250 -0.1133 0.04147 0.03222 -0.0012 1.0000 0.9851
-1.000 -0.1039 0.04131 0.03197 -0.0002 1.0000 0.9864
-0.750 -0.0953 0.04119 0.03176 0.0010 1.0000 0.9875
-0.500 -0.0863 0.04109 0.03159 0.0021 1.0000 0.9887
-0.250 -0.0775 0.04102 0.03144 0.0033 1.0000 0.9899
0.000 -0.0688 0.04097 0.03133 0.0044 1.0000 0.9911
0.250 -0.0588 0.04097 0.03127 0.0053 1.0000 0.9927
0.500 -0.0489 0.04098 0.03124 0.0063 1.0000 0.9941
0.750 -0.0373 0.04101 0.03123 0.0068 1.0000 0.9957
1.000 -0.0236 0.04114 0.03131 0.0069 1.0000 0.9981
1.250 -0.0121 0.04129 0.03144 0.0074 1.0000 1.0000
1.500 -0.0087 0.04123 0.03136 0.0095 1.0000 1.0000
1.750 -0.0057 0.04117 0.03129 0.0115 1.0000 1.0000
2.000 -0.0032 0.04108 0.03121 0.0136 1.0000 1.0000
2.250 -0.0011 0.04097 0.03109 0.0157 1.0000 1.0000
2.500 0.0005 0.04084 0.03098 0.0178 1.0000 1.0000
2.750 0.0015 0.04068 0.03084 0.0200 1.0000 1.0000
3.000 0.0022 0.04051 0.03068 0.0221 1.0000 1.0000
3.250 0.0030 0.04032 0.03053 0.0241 1.0000 1.0000
3.500 0.0043 0.04018 0.03041 0.0259 1.0000 1.0000
3.750 0.0091 0.04024 0.03050 0.0270 1.0000 1.0000
4.000 0.0190 0.04064 0.03093 0.0270 1.0000 1.0000
4.250 0.0329 0.04135 0.03168 0.0261 1.0000 1.0000
4.500 0.0493 0.04232 0.03270 0.0246 1.0000 1.0000
4.750 0.3026 0.04843 0.03895 -0.0086 0.8112 1.0000
5.000 0.3528 0.04844 0.03907 -0.0114 0.7779 1.0000
5.250 0.4006 0.04817 0.03893 -0.0136 0.7478 1.0000
5.500 0.4577 0.04738 0.03829 -0.0163 0.7197 1.0000
5.750 0.5131 0.04602 0.03715 -0.0181 0.6921 1.0000
6.000 0.5599 0.04431 0.03563 -0.0184 0.6625 1.0000
6.250 0.6186 0.04127 0.03287 -0.0187 0.6317 1.0000
6.500 0.6999 0.03550 0.02743 -0.0187 0.5969 1.0000
6.750 0.7526 0.03079 0.02283 -0.0164 0.5358 1.0000
7.000 0.8207 0.02766 0.01895 -0.0170 0.4454 1.0000
7.250 0.8617 0.02853 0.01914 -0.0186 0.3959 1.0000
7.500 0.9008 0.02986 0.02019 -0.0209 0.3648 1.0000
7.750 0.9398 0.03134 0.02161 -0.0234 0.3439 1.0000
8.000 0.9761 0.03289 0.02313 -0.0256 0.3268 1.0000
8.250 1.0126 0.03455 0.02481 -0.0279 0.3127 1.0000
8.500 1.0509 0.03639 0.02666 -0.0305 0.3014 1.0000
8.750 1.0734 0.03830 0.02887 -0.0310 0.2921 1.0000
9.000 1.1053 0.04038 0.03101 -0.0328 0.2826 1.0000
9.250 1.1247 0.04261 0.03359 -0.0329 0.2755 1.0000
9.500 1.1550 0.04503 0.03605 -0.0345 0.2679 1.0000
9.750 1.1603 0.04759 0.03906 -0.0329 0.2620 1.0000
10.000 1.1880 0.05007 0.04162 -0.0340 0.2547 1.0000
10.250 1.1899 0.05323 0.04515 -0.0323 0.2508 1.0000
10.500 1.1802 0.05659 0.04890 -0.0297 0.2472 1.0000
10.750 1.1750 0.05991 0.05249 -0.0276 0.2431 1.0000
11.000 1.2012 0.06304 0.05563 -0.0285 0.2368 1.0000
11.250 1.1712 0.06736 0.06027 -0.0248 0.2362 1.0000
11.500 1.1350 0.07212 0.06522 -0.0214 0.2364 1.0000
11.750 1.0949 0.07813 0.07137 -0.0195 0.2372 1.0000
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Polar data table (+)
Polar graphs
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