SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il) Reynolds number: 200,000 Max Cl/Cd: 59.56 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s102s-il-200000.txt Download as CSV file: xf-s102s-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4154 0.09245 0.08901 -0.0561 1.0000 0.0507
-10.250 -0.4341 0.08570 0.08230 -0.0601 1.0000 0.0513
-10.000 -0.4582 0.08013 0.07675 -0.0624 1.0000 0.0513
-9.750 -0.4854 0.07591 0.07253 -0.0628 1.0000 0.0513
-9.500 -0.5145 0.07292 0.06956 -0.0611 1.0000 0.0511
-9.250 -0.5478 0.07167 0.06838 -0.0567 1.0000 0.0505
-9.000 -0.5590 0.06635 0.06282 -0.0641 0.9893 0.0517
-8.750 -0.5723 0.06049 0.05616 -0.0722 0.9731 0.0547
-8.500 -0.5423 0.05535 0.05123 -0.0751 0.9709 0.0564
-8.250 -0.5221 0.05218 0.04799 -0.0772 0.9622 0.0585
-7.250 -0.4346 0.03174 0.02519 -0.0811 0.9328 0.0313
-7.000 -0.3988 0.02848 0.02160 -0.0825 0.9297 0.0276
-6.750 -0.3710 0.02565 0.01823 -0.0816 0.9217 0.0253
-6.500 -0.3362 0.02379 0.01619 -0.0826 0.9171 0.0252
-6.250 -0.3000 0.02210 0.01448 -0.0839 0.9138 0.0260
-6.000 -0.2753 0.02104 0.01339 -0.0833 0.9047 0.0268
-5.750 -0.2435 0.02010 0.01238 -0.0840 0.8998 0.0295
-5.500 -0.2222 0.01911 0.01147 -0.0831 0.8913 0.0331
-5.250 -0.1965 0.01821 0.01050 -0.0829 0.8853 0.0359
-5.000 -0.1787 0.01720 0.00953 -0.0818 0.8772 0.0408
-4.750 -0.1566 0.01630 0.00861 -0.0814 0.8706 0.0520
-4.500 -0.1408 0.01478 0.00744 -0.0806 0.8633 0.1138
-4.250 -0.1332 0.01339 0.00800 -0.0784 0.8557 0.5873
-4.000 -0.1040 0.01483 0.00942 -0.0766 0.8519 0.6218
-3.750 -0.0808 0.01620 0.01083 -0.0737 0.8460 0.6434
-3.500 -0.0558 0.01741 0.01204 -0.0710 0.8414 0.6614
-3.250 -0.0313 0.01891 0.01356 -0.0672 0.8378 0.6822
-3.000 -0.0068 0.02014 0.01478 -0.0636 0.8344 0.6984
-2.750 0.0162 0.02027 0.01487 -0.0621 0.8291 0.7018
-2.500 0.0423 0.02005 0.01454 -0.0623 0.8247 0.7045
-2.250 0.0707 0.01972 0.01408 -0.0632 0.8214 0.7075
-2.000 0.0988 0.01935 0.01358 -0.0647 0.8180 0.7107
-1.750 0.1238 0.01907 0.01322 -0.0654 0.8136 0.7130
-1.500 0.1496 0.01893 0.01303 -0.0654 0.8099 0.7143
-1.250 0.1776 0.01875 0.01278 -0.0658 0.8066 0.7154
-1.000 0.2066 0.01862 0.01258 -0.0663 0.8040 0.7168
-0.750 0.2319 0.01856 0.01250 -0.0666 0.8006 0.7182
-0.500 0.2572 0.01850 0.01242 -0.0669 0.7968 0.7193
-0.250 0.2846 0.01842 0.01230 -0.0675 0.7934 0.7210
0.000 0.3141 0.01829 0.01213 -0.0684 0.7906 0.7223
0.250 0.3445 0.01819 0.01198 -0.0696 0.7883 0.7233
0.500 0.3710 0.01818 0.01196 -0.0701 0.7844 0.7247
0.750 0.3980 0.01804 0.01179 -0.0705 0.7776 0.7263
1.000 0.4336 0.01762 0.01124 -0.0718 0.7709 0.7273
1.250 0.4589 0.01738 0.01099 -0.0716 0.7605 0.7283
1.500 0.4892 0.01705 0.01060 -0.0719 0.7527 0.7291
1.750 0.5159 0.01677 0.01031 -0.0715 0.7426 0.7300
2.000 0.5430 0.01654 0.01006 -0.0712 0.7330 0.7313
2.250 0.5719 0.01631 0.00980 -0.0712 0.7249 0.7326
2.500 0.5987 0.01620 0.00972 -0.0712 0.7175 0.7337
2.750 0.6271 0.01603 0.00955 -0.0713 0.7099 0.7348
3.000 0.6547 0.01588 0.00942 -0.0714 0.7016 0.7360
3.250 0.6831 0.01570 0.00924 -0.0715 0.6931 0.7373
3.500 0.7098 0.01556 0.00915 -0.0714 0.6838 0.7387
3.750 0.7396 0.01533 0.00889 -0.0717 0.6739 0.7402
4.000 0.7651 0.01514 0.00873 -0.0713 0.6606 0.7420
4.250 0.7910 0.01494 0.00855 -0.0709 0.6452 0.7438
4.500 0.8154 0.01470 0.00834 -0.0700 0.6272 0.7452
4.750 0.8368 0.01452 0.00822 -0.0687 0.6016 0.7466
5.000 0.8559 0.01437 0.00804 -0.0668 0.5536 0.7481
5.250 0.8551 0.01508 0.00792 -0.0613 0.4070 0.7498
5.500 0.8509 0.01646 0.00865 -0.0562 0.3073 0.7516
5.750 0.8579 0.01741 0.00928 -0.0531 0.2629 0.7535
6.000 0.8692 0.01815 0.00983 -0.0508 0.2395 0.7556
6.250 0.8829 0.01876 0.01034 -0.0488 0.2247 0.7577
6.500 0.8993 0.01932 0.01085 -0.0473 0.2138 0.7599
6.750 0.9137 0.01996 0.01142 -0.0454 0.2057 0.7620
7.000 0.9325 0.02042 0.01195 -0.0441 0.1982 0.7645
7.250 0.9506 0.02113 0.01258 -0.0430 0.1915 0.7672
7.500 0.9716 0.02161 0.01314 -0.0423 0.1857 0.7700
7.750 0.9930 0.02218 0.01371 -0.0417 0.1805 0.7729
8.000 1.0185 0.02301 0.01444 -0.0419 0.1753 0.7757
8.250 1.0388 0.02344 0.01503 -0.0410 0.1711 0.7785
8.500 1.0600 0.02398 0.01563 -0.0403 0.1665 0.7817
8.750 1.0855 0.02470 0.01634 -0.0404 0.1622 0.7852
9.000 1.1116 0.02545 0.01716 -0.0406 0.1582 0.7892
9.250 1.1322 0.02600 0.01785 -0.0399 0.1542 0.7932
9.500 1.1539 0.02660 0.01853 -0.0394 0.1503 0.7975
9.750 1.1887 0.02773 0.01960 -0.0411 0.1454 0.8025
10.000 1.2036 0.02824 0.02033 -0.0395 0.1424 0.8085
10.250 1.2205 0.02884 0.02111 -0.0382 0.1386 0.8147
10.500 1.2400 0.02949 0.02180 -0.0375 0.1348 0.8224
10.750 1.2692 0.03063 0.02299 -0.0383 0.1302 0.8293
11.000 1.2792 0.03120 0.02381 -0.0361 0.1271 0.8395
11.250 1.2913 0.03183 0.02463 -0.0343 0.1234 0.8520
11.500 1.3053 0.03239 0.02527 -0.0327 0.1198 0.8700
11.750 1.3222 0.03330 0.02633 -0.0314 0.1158 0.9096
12.000 1.3285 0.03399 0.02730 -0.0295 0.1124 1.0000
12.250 1.3389 0.03485 0.02824 -0.0283 0.1085 1.0000
12.500 1.3540 0.03570 0.02902 -0.0277 0.1048 1.0000
12.750 1.3630 0.03701 0.03049 -0.0264 0.1010 1.0000
13.000 1.3664 0.03815 0.03181 -0.0245 0.0973 1.0000
13.250 1.3725 0.03913 0.03282 -0.0232 0.0938 1.0000
13.500 1.3834 0.04043 0.03409 -0.0224 0.0900 1.0000
13.750 1.3817 0.04202 0.03595 -0.0207 0.0866 1.0000
14.000 1.3843 0.04341 0.03744 -0.0196 0.0829 1.0000
14.250 1.3904 0.04481 0.03877 -0.0189 0.0794 1.0000
14.500 1.3896 0.04692 0.04113 -0.0179 0.0759 1.0000
14.750 1.3905 0.04885 0.04318 -0.0172 0.0722 1.0000
15.000 1.3927 0.05079 0.04508 -0.0168 0.0689 1.0000
15.250 1.3913 0.05341 0.04793 -0.0164 0.0653 1.0000
15.500 1.3908 0.05592 0.05056 -0.0163 0.0618 1.0000
15.750 1.3903 0.05858 0.05316 -0.0163 0.0586 1.0000
16.000 1.3860 0.06196 0.05682 -0.0165 0.0555 1.0000
16.250 1.3828 0.06524 0.06022 -0.0170 0.0525 1.0000
16.500 1.3787 0.06873 0.06366 -0.0175 0.0498 1.0000
16.750 1.3707 0.07310 0.06829 -0.0185 0.0475 1.0000
17.000 1.3631 0.07750 0.07285 -0.0197 0.0452 1.0000
17.250 1.3558 0.08198 0.07740 -0.0213 0.0432 1.0000
17.500 1.3470 0.08680 0.08225 -0.0228 0.0412 1.0000
17.750 1.3336 0.09280 0.08851 -0.0254 0.0398 1.0000
18.000 1.3208 0.09890 0.09480 -0.0283 0.0384 1.0000
18.250 1.3092 0.10495 0.10098 -0.0314 0.0371 1.0000
18.500 1.2999 0.11065 0.10673 -0.0345 0.0358 1.0000
18.750 1.2917 0.11602 0.11212 -0.0370 0.0344 1.0000
19.000 1.2732 0.12407 0.12042 -0.0419 0.0339 1.0000
19.250 1.2534 0.13261 0.12918 -0.0472 0.0334 1.0000
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