SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il) Reynolds number: 500,000 Max Cl/Cd: 69.83 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s102s-il-500000-n5.txt Download as CSV file: xf-s102s-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5822 0.06174 0.05893 -0.0703 1.0000 0.0055
-11.750 -0.6060 0.05681 0.05389 -0.0712 1.0000 0.0055
-11.500 -0.6243 0.05235 0.04929 -0.0722 0.9994 0.0054
-11.250 -0.6352 0.04672 0.04341 -0.0762 0.9949 0.0054
-11.000 -0.6444 0.04174 0.03816 -0.0789 0.9889 0.0054
-10.750 -0.6456 0.03710 0.03317 -0.0819 0.9838 0.0053
-10.500 -0.6426 0.03357 0.02934 -0.0832 0.9757 0.0053
-10.250 -0.6318 0.03041 0.02585 -0.0847 0.9682 0.0053
-10.000 -0.6166 0.02795 0.02312 -0.0857 0.9589 0.0053
-9.500 -0.5830 0.02416 0.01883 -0.0855 0.9311 0.0053
-9.250 -0.5596 0.02261 0.01704 -0.0859 0.9128 0.0053
-9.000 -0.5361 0.02136 0.01557 -0.0861 0.8893 0.0053
-8.750 -0.5159 0.02034 0.01431 -0.0854 0.8658 0.0054
-8.500 -0.4979 0.01948 0.01326 -0.0842 0.8458 0.0054
-8.250 -0.4799 0.01876 0.01238 -0.0830 0.8294 0.0055
-8.000 -0.4632 0.01792 0.01139 -0.0817 0.8156 0.0055
-7.500 -0.4279 0.01654 0.00980 -0.0793 0.7923 0.0057
-7.250 -0.4087 0.01595 0.00913 -0.0784 0.7830 0.0059
-7.000 -0.3885 0.01543 0.00852 -0.0776 0.7743 0.0060
-6.750 -0.3672 0.01494 0.00797 -0.0769 0.7671 0.0062
-6.500 -0.3453 0.01447 0.00743 -0.0763 0.7601 0.0064
-6.250 -0.3228 0.01404 0.00692 -0.0758 0.7541 0.0068
-6.000 -0.2993 0.01362 0.00644 -0.0754 0.7483 0.0071
-5.750 -0.2753 0.01325 0.00599 -0.0751 0.7428 0.0076
-5.500 -0.2513 0.01285 0.00555 -0.0748 0.7380 0.0085
-5.250 -0.2259 0.01253 0.00518 -0.0746 0.7333 0.0093
-5.000 -0.2004 0.01220 0.00482 -0.0745 0.7286 0.0109
-4.750 -0.1745 0.01193 0.00450 -0.0744 0.7242 0.0133
-4.500 -0.1485 0.01163 0.00421 -0.0745 0.7202 0.0192
-4.250 -0.1220 0.01132 0.00394 -0.0745 0.7162 0.0302
-4.000 -0.0956 0.01100 0.00368 -0.0746 0.7126 0.0485
-3.750 -0.0700 0.01049 0.00338 -0.0748 0.7092 0.1033
-3.500 -0.0474 0.00917 0.00276 -0.0754 0.7062 0.2970
-3.250 -0.0232 0.00810 0.00257 -0.0759 0.7031 0.5517
-3.000 0.0058 0.00823 0.00268 -0.0760 0.7001 0.5716
-2.750 0.0349 0.00839 0.00277 -0.0762 0.6972 0.5855
-2.500 0.0636 0.00868 0.00302 -0.0762 0.6944 0.6009
-2.250 0.0923 0.00873 0.00304 -0.0763 0.6917 0.6043
-2.000 0.1214 0.00871 0.00296 -0.0766 0.6892 0.6050
-1.750 0.1506 0.00869 0.00290 -0.0769 0.6867 0.6058
-1.500 0.1797 0.00867 0.00285 -0.0773 0.6843 0.6065
-1.250 0.2088 0.00867 0.00281 -0.0776 0.6819 0.6075
-1.000 0.2378 0.00867 0.00277 -0.0779 0.6797 0.6085
-0.750 0.2669 0.00868 0.00274 -0.0782 0.6773 0.6093
-0.500 0.2956 0.00870 0.00270 -0.0784 0.6734 0.6101
-0.250 0.3240 0.00867 0.00266 -0.0786 0.6669 0.6109
0.000 0.3522 0.00869 0.00261 -0.0787 0.6600 0.6117
0.250 0.3805 0.00869 0.00259 -0.0789 0.6530 0.6125
0.500 0.4087 0.00870 0.00256 -0.0790 0.6460 0.6133
0.750 0.4370 0.00872 0.00255 -0.0791 0.6401 0.6141
1.000 0.4651 0.00873 0.00255 -0.0792 0.6321 0.6148
1.250 0.4929 0.00876 0.00254 -0.0793 0.6232 0.6156
1.500 0.5203 0.00878 0.00254 -0.0792 0.6125 0.6166
1.750 0.5479 0.00880 0.00255 -0.0793 0.6012 0.6175
2.000 0.5751 0.00883 0.00258 -0.0792 0.5886 0.6183
2.250 0.6021 0.00888 0.00260 -0.0791 0.5728 0.6192
2.500 0.6278 0.00899 0.00264 -0.0787 0.5468 0.6200
2.750 0.6474 0.00939 0.00274 -0.0773 0.4745 0.6209
3.000 0.6613 0.01028 0.00314 -0.0750 0.3759 0.6218
3.250 0.6798 0.01092 0.00349 -0.0736 0.3117 0.6227
3.500 0.7003 0.01142 0.00379 -0.0725 0.2664 0.6237
3.750 0.7220 0.01183 0.00404 -0.0716 0.2337 0.6248
4.000 0.7445 0.01217 0.00428 -0.0709 0.2094 0.6258
4.500 0.7903 0.01279 0.00475 -0.0695 0.1770 0.6280
4.750 0.8136 0.01305 0.00498 -0.0688 0.1662 0.6291
5.000 0.8366 0.01332 0.00521 -0.0682 0.1581 0.6301
5.250 0.8600 0.01356 0.00545 -0.0675 0.1517 0.6312
5.750 0.9053 0.01406 0.00596 -0.0660 0.1418 0.6337
6.000 0.9276 0.01430 0.00624 -0.0652 0.1376 0.6350
6.250 0.9486 0.01460 0.00654 -0.0642 0.1331 0.6364
6.500 0.9693 0.01487 0.00683 -0.0631 0.1297 0.6377
6.750 0.9895 0.01510 0.00712 -0.0619 0.1271 0.6391
7.000 1.0087 0.01537 0.00743 -0.0605 0.1244 0.6405
7.250 1.0276 0.01569 0.00777 -0.0592 0.1217 0.6420
7.500 1.0457 0.01606 0.00816 -0.0577 0.1187 0.6436
7.750 1.0639 0.01644 0.00857 -0.0563 0.1161 0.6452
8.000 1.0836 0.01676 0.00894 -0.0552 0.1143 0.6467
8.250 1.1027 0.01711 0.00935 -0.0540 0.1119 0.6482
8.500 1.1212 0.01749 0.00978 -0.0527 0.1094 0.6499
8.750 1.1387 0.01792 0.01025 -0.0514 0.1069 0.6516
9.000 1.1549 0.01843 0.01079 -0.0499 0.1042 0.6535
9.250 1.1724 0.01888 0.01131 -0.0486 0.1023 0.6555
9.500 1.1909 0.01929 0.01181 -0.0475 0.1003 0.6577
9.750 1.2087 0.01975 0.01233 -0.0463 0.0978 0.6600
10.000 1.2257 0.02027 0.01288 -0.0451 0.0951 0.6624
10.500 1.2570 0.02148 0.01420 -0.0426 0.0898 0.6676
10.750 1.2744 0.02200 0.01482 -0.0415 0.0875 0.6705
11.000 1.2908 0.02260 0.01549 -0.0405 0.0845 0.6737
11.250 1.3061 0.02329 0.01621 -0.0394 0.0812 0.6770
11.500 1.3209 0.02403 0.01700 -0.0382 0.0781 0.6802
11.750 1.3368 0.02471 0.01777 -0.0373 0.0746 0.6837
12.000 1.3512 0.02551 0.01861 -0.0362 0.0701 0.6877
12.250 1.3653 0.02636 0.01951 -0.0352 0.0660 0.6921
12.750 1.3910 0.02829 0.02153 -0.0331 0.0571 0.7017
13.000 1.4032 0.02934 0.02264 -0.0321 0.0522 0.7075
13.250 1.4140 0.03052 0.02387 -0.0311 0.0484 0.7136
13.500 1.4248 0.03173 0.02515 -0.0301 0.0444 0.7206
14.000 1.4437 0.03444 0.02801 -0.0283 0.0372 0.7380
14.250 1.4514 0.03599 0.02963 -0.0273 0.0339 0.7488
14.500 1.4595 0.03751 0.03126 -0.0265 0.0308 0.7630
14.750 1.4654 0.03924 0.03310 -0.0256 0.0281 0.7818
15.000 1.4717 0.04091 0.03494 -0.0248 0.0257 0.8111
15.250 1.4750 0.04265 0.03698 -0.0237 0.0231 0.9318
15.500 1.4789 0.04459 0.03900 -0.0230 0.0211 1.0000
15.750 1.4810 0.04699 0.04144 -0.0226 0.0187 1.0000
16.000 1.4834 0.04942 0.04394 -0.0223 0.0165 1.0000
16.250 1.4844 0.05208 0.04668 -0.0221 0.0152 1.0000
16.500 1.4859 0.05476 0.04946 -0.0221 0.0139 1.0000
16.750 1.4835 0.05798 0.05274 -0.0222 0.0124 1.0000
17.000 1.4826 0.06114 0.05601 -0.0225 0.0115 1.0000
17.250 1.4806 0.06454 0.05953 -0.0231 0.0108 1.0000
17.500 1.4746 0.06858 0.06368 -0.0239 0.0099 1.0000
17.750 1.4686 0.07281 0.06803 -0.0250 0.0093 1.0000
18.000 1.4624 0.07725 0.07260 -0.0264 0.0090 1.0000
18.250 1.4532 0.08233 0.07783 -0.0283 0.0086 1.0000
18.500 1.4409 0.08814 0.08378 -0.0307 0.0081 1.0000
18.750 1.4263 0.09464 0.09044 -0.0337 0.0080 1.0000
19.000 1.4080 0.10211 0.09809 -0.0374 0.0078 1.0000
19.250 1.3857 0.11064 0.10680 -0.0420 0.0077 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SOMERS S102 AIRFOIL (SHARP) (s102s-il)