SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il) Reynolds number: 200,000 Max Cl/Cd: 57.02 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s102s-il-200000-n5.txt Download as CSV file: xf-s102s-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4472 0.08546 0.08180 -0.0602 1.0000 0.0118
-11.000 -0.4732 0.07642 0.07271 -0.0652 1.0000 0.0115
-10.750 -0.5015 0.06983 0.06605 -0.0676 1.0000 0.0113
-10.500 -0.5297 0.06467 0.06079 -0.0681 1.0000 0.0111
-10.000 -0.6031 0.04927 0.04458 -0.0709 0.9906 0.0100
-9.750 -0.6011 0.04524 0.04026 -0.0738 0.9811 0.0100
-9.500 -0.5926 0.04145 0.03613 -0.0759 0.9719 0.0100
-9.250 -0.5829 0.03808 0.03241 -0.0765 0.9611 0.0099
-9.000 -0.5690 0.03514 0.02912 -0.0768 0.9505 0.0099
-8.750 -0.5507 0.03229 0.02588 -0.0772 0.9409 0.0100
-8.500 -0.5298 0.02984 0.02307 -0.0773 0.9302 0.0100
-8.250 -0.5068 0.02784 0.02079 -0.0773 0.9189 0.0101
-8.000 -0.4801 0.02610 0.01888 -0.0780 0.9094 0.0103
-7.750 -0.4514 0.02468 0.01731 -0.0788 0.9000 0.0105
-7.500 -0.4238 0.02345 0.01595 -0.0793 0.8894 0.0109
-7.250 -0.3955 0.02229 0.01466 -0.0798 0.8796 0.0113
-7.000 -0.3687 0.02123 0.01347 -0.0799 0.8692 0.0118
-6.750 -0.3448 0.02030 0.01242 -0.0796 0.8582 0.0123
-6.500 -0.3219 0.01945 0.01143 -0.0792 0.8482 0.0129
-6.250 -0.3000 0.01880 0.01076 -0.0788 0.8380 0.0141
-6.000 -0.2783 0.01822 0.01008 -0.0782 0.8285 0.0156
-5.750 -0.2570 0.01757 0.00935 -0.0777 0.8202 0.0172
-5.500 -0.2362 0.01697 0.00867 -0.0769 0.8118 0.0192
-5.250 -0.2142 0.01637 0.00798 -0.0764 0.8050 0.0214
-5.000 -0.1919 0.01584 0.00740 -0.0760 0.7985 0.0264
-4.750 -0.1689 0.01532 0.00686 -0.0756 0.7923 0.0354
-4.500 -0.1458 0.01470 0.00631 -0.0754 0.7874 0.0576
-4.250 -0.1252 0.01380 0.00575 -0.0751 0.7817 0.1320
-4.000 -0.1142 0.01186 0.00561 -0.0742 0.7761 0.5298
-3.750 -0.0854 0.01230 0.00590 -0.0741 0.7719 0.5795
-3.500 -0.0578 0.01278 0.00629 -0.0736 0.7673 0.6018
-3.250 -0.0314 0.01351 0.00704 -0.0723 0.7629 0.6214
-3.000 -0.0045 0.01404 0.00753 -0.0714 0.7591 0.6358
-2.750 0.0240 0.01404 0.00742 -0.0715 0.7560 0.6383
-2.500 0.0524 0.01396 0.00722 -0.0718 0.7526 0.6398
-2.250 0.0806 0.01387 0.00704 -0.0721 0.7489 0.6414
-2.000 0.1091 0.01377 0.00684 -0.0725 0.7455 0.6426
-1.750 0.1379 0.01369 0.00665 -0.0729 0.7422 0.6442
-1.500 0.1672 0.01363 0.00646 -0.0734 0.7394 0.6458
-1.250 0.1959 0.01356 0.00631 -0.0739 0.7364 0.6471
-1.000 0.2244 0.01350 0.00619 -0.0743 0.7333 0.6482
-0.750 0.2528 0.01347 0.00613 -0.0746 0.7303 0.6490
-0.500 0.2812 0.01346 0.00609 -0.0749 0.7276 0.6499
-0.250 0.3098 0.01346 0.00606 -0.0752 0.7251 0.6509
0.000 0.3389 0.01347 0.00603 -0.0755 0.7227 0.6519
0.250 0.3667 0.01349 0.00605 -0.0757 0.7198 0.6529
0.500 0.3943 0.01349 0.00607 -0.0759 0.7157 0.6539
0.750 0.4224 0.01345 0.00598 -0.0760 0.7093 0.6549
1.000 0.4494 0.01340 0.00591 -0.0758 0.7008 0.6560
1.250 0.4771 0.01333 0.00578 -0.0758 0.6915 0.6571
1.500 0.5034 0.01329 0.00574 -0.0755 0.6822 0.6583
1.750 0.5314 0.01325 0.00564 -0.0756 0.6739 0.6597
2.000 0.5575 0.01322 0.00563 -0.0753 0.6636 0.6613
2.250 0.5843 0.01319 0.00558 -0.0751 0.6528 0.6627
2.500 0.6111 0.01316 0.00550 -0.0749 0.6410 0.6640
2.750 0.6371 0.01314 0.00551 -0.0746 0.6288 0.6650
3.000 0.6629 0.01314 0.00555 -0.0743 0.6170 0.6660
3.250 0.6887 0.01315 0.00559 -0.0739 0.6044 0.6671
3.500 0.7140 0.01317 0.00565 -0.0735 0.5885 0.6683
3.750 0.7384 0.01320 0.00568 -0.0728 0.5645 0.6695
4.000 0.7595 0.01332 0.00564 -0.0715 0.5085 0.6709
4.250 0.7670 0.01409 0.00579 -0.0678 0.4032 0.6723
4.500 0.7760 0.01500 0.00630 -0.0648 0.3272 0.6738
4.750 0.7893 0.01573 0.00677 -0.0626 0.2767 0.6754
5.000 0.8056 0.01632 0.00719 -0.0610 0.2441 0.6773
5.250 0.8229 0.01684 0.00760 -0.0595 0.2218 0.6792
5.500 0.8409 0.01731 0.00800 -0.0581 0.2053 0.6810
5.750 0.8586 0.01774 0.00841 -0.0566 0.1926 0.6824
6.000 0.8760 0.01813 0.00881 -0.0550 0.1826 0.6839
6.250 0.8915 0.01858 0.00925 -0.0532 0.1748 0.6856
6.500 0.9091 0.01897 0.00968 -0.0517 0.1683 0.6875
6.750 0.9254 0.01946 0.01017 -0.0501 0.1629 0.6894
7.000 0.9425 0.01995 0.01070 -0.0487 0.1584 0.6915
7.250 0.9609 0.02042 0.01122 -0.0474 0.1541 0.6938
7.500 0.9780 0.02095 0.01177 -0.0461 0.1498 0.6961
7.750 0.9931 0.02158 0.01241 -0.0445 0.1460 0.6980
8.000 1.0113 0.02206 0.01300 -0.0434 0.1427 0.7002
8.250 1.0292 0.02259 0.01362 -0.0422 0.1396 0.7026
8.500 1.0465 0.02317 0.01426 -0.0411 0.1363 0.7055
8.750 1.0626 0.02384 0.01495 -0.0398 0.1332 0.7087
9.000 1.0790 0.02456 0.01570 -0.0387 0.1303 0.7120
9.250 1.0972 0.02511 0.01640 -0.0377 0.1276 0.7150
9.500 1.1148 0.02572 0.01713 -0.0367 0.1247 0.7183
9.750 1.1317 0.02637 0.01787 -0.0357 0.1217 0.7219
10.000 1.1475 0.02713 0.01868 -0.0346 0.1189 0.7259
10.250 1.1637 0.02796 0.01955 -0.0337 0.1163 0.7298
10.500 1.1812 0.02860 0.02037 -0.0328 0.1135 0.7340
10.750 1.1980 0.02932 0.02123 -0.0319 0.1105 0.7389
11.250 1.2274 0.03099 0.02307 -0.0300 0.1046 0.7500
11.500 1.2425 0.03189 0.02408 -0.0291 0.1019 0.7569
11.750 1.2579 0.03270 0.02509 -0.0283 0.0987 0.7645
12.000 1.2718 0.03359 0.02613 -0.0274 0.0955 0.7740
12.250 1.2836 0.03460 0.02725 -0.0264 0.0925 0.7853
12.500 1.2951 0.03568 0.02847 -0.0254 0.0896 0.8001
12.750 1.3081 0.03660 0.02964 -0.0245 0.0860 0.8214
13.000 1.3174 0.03754 0.03082 -0.0231 0.0826 0.8626
13.250 1.3224 0.03863 0.03204 -0.0216 0.0797 1.0000
13.500 1.3347 0.03992 0.03346 -0.0212 0.0761 1.0000
13.750 1.3456 0.04128 0.03496 -0.0207 0.0719 1.0000
14.000 1.3526 0.04298 0.03668 -0.0202 0.0684 1.0000
14.250 1.3635 0.04446 0.03832 -0.0198 0.0640 1.0000
14.500 1.3703 0.04630 0.04021 -0.0195 0.0599 1.0000
14.750 1.3768 0.04824 0.04225 -0.0191 0.0561 1.0000
15.000 1.3822 0.05034 0.04445 -0.0189 0.0521 1.0000
15.250 1.3844 0.05282 0.04699 -0.0187 0.0489 1.0000
15.500 1.3880 0.05524 0.04955 -0.0186 0.0454 1.0000
15.750 1.3874 0.05819 0.05258 -0.0188 0.0425 1.0000
16.000 1.3868 0.06127 0.05579 -0.0190 0.0399 1.0000
16.250 1.3849 0.06459 0.05926 -0.0194 0.0375 1.0000
16.500 1.3791 0.06853 0.06331 -0.0202 0.0355 1.0000
16.750 1.3726 0.07276 0.06767 -0.0213 0.0338 1.0000
17.000 1.3660 0.07719 0.07228 -0.0226 0.0321 1.0000
17.250 1.3558 0.08233 0.07757 -0.0244 0.0306 1.0000
17.500 1.3421 0.08831 0.08370 -0.0269 0.0296 1.0000
17.750 1.3254 0.09514 0.09069 -0.0301 0.0289 1.0000
18.000 1.3073 0.10257 0.09829 -0.0339 0.0283 1.0000
18.250 1.2880 0.11057 0.10650 -0.0382 0.0277 1.0000
18.500 1.2657 0.11952 0.11565 -0.0434 0.0274 1.0000
18.750 1.2413 0.12917 0.12548 -0.0491 0.0273 1.0000
19.000 1.2166 0.13902 0.13549 -0.0550 0.0271 1.0000
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Polar data table (+)
Polar graphs
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