REPUBLIC S-3 AIRFOIL (s3-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: REPUBLIC S-3 AIRFOIL (s3-il) Reynolds number: 100,000 Max Cl/Cd: 38.54 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3-il-100000.txt Download as CSV file: xf-s3-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: REPUBLIC S-3 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4606 0.08924 0.08500 -0.0106 1.0000 0.1238
-9.000 -0.5340 0.09121 0.08667 -0.0071 1.0000 0.1161
-8.750 -0.5434 0.08660 0.08214 -0.0109 1.0000 0.1214
-8.500 -0.5758 0.08072 0.07631 -0.0182 1.0000 0.1232
-8.250 -0.6203 0.07734 0.07269 -0.0222 1.0000 0.1246
-8.000 -0.5719 0.07301 0.06867 -0.0181 1.0000 0.1329
-7.750 -0.6197 0.06998 0.06518 -0.0223 1.0000 0.1394
-7.500 -0.5824 0.06513 0.06073 -0.0199 1.0000 0.1472
-7.250 -0.5873 0.06132 0.05684 -0.0203 1.0000 0.1585
-7.000 -0.5843 0.05819 0.05366 -0.0198 1.0000 0.1727
-6.750 -0.5728 0.05585 0.05138 -0.0182 1.0000 0.1916
-5.750 -0.5225 0.03542 0.02800 -0.0146 1.0000 0.0796
-5.500 -0.5049 0.03195 0.02431 -0.0128 1.0000 0.0745
-5.250 -0.4868 0.02946 0.02114 -0.0101 1.0000 0.0694
-5.000 -0.4689 0.02743 0.01896 -0.0083 1.0000 0.0706
-4.750 -0.4522 0.02594 0.01742 -0.0065 1.0000 0.0738
-4.500 -0.4354 0.02449 0.01578 -0.0044 1.0000 0.0752
-4.250 -0.4183 0.02316 0.01428 -0.0023 1.0000 0.0770
-4.000 -0.4017 0.02228 0.01320 -0.0003 1.0000 0.0804
-3.750 -0.3848 0.02086 0.01188 0.0013 1.0000 0.0859
-3.500 -0.3677 0.01995 0.01099 0.0031 1.0000 0.0918
-3.250 -0.3515 0.01901 0.01014 0.0048 1.0000 0.1001
-3.000 -0.3354 0.01831 0.00947 0.0065 1.0000 0.1113
-2.750 -0.2962 0.01714 0.00844 0.0037 0.9911 0.1406
-2.500 -0.2756 0.01415 0.00820 0.0048 0.9822 0.6412
-2.250 -0.2452 0.01446 0.00887 0.0070 0.9705 0.7819
-2.000 -0.2072 0.01483 0.00922 0.0073 0.9575 0.8411
-1.750 -0.1582 0.01530 0.00960 0.0061 0.9453 0.8876
-1.500 -0.0738 0.01597 0.01005 -0.0012 0.9400 0.9255
-1.250 0.0016 0.01593 0.00982 -0.0096 0.9307 0.9352
-1.000 0.0708 0.01571 0.00944 -0.0171 0.9190 0.9452
-0.750 0.1282 0.01542 0.00903 -0.0224 0.9020 0.9563
-0.500 0.1815 0.01505 0.00851 -0.0266 0.8793 0.9664
-0.250 0.2266 0.01466 0.00798 -0.0293 0.8513 0.9777
0.000 0.2686 0.01426 0.00745 -0.0316 0.8205 0.9897
0.250 0.3070 0.01391 0.00696 -0.0336 0.7898 1.0000
0.500 0.3213 0.01378 0.00668 -0.0311 0.7620 1.0000
0.750 0.3362 0.01369 0.00646 -0.0287 0.7327 1.0000
1.000 0.3518 0.01363 0.00626 -0.0265 0.7012 1.0000
1.250 0.3679 0.01358 0.00608 -0.0243 0.6658 1.0000
1.500 0.3844 0.01355 0.00588 -0.0222 0.6288 1.0000
1.750 0.4012 0.01356 0.00572 -0.0201 0.5882 1.0000
2.000 0.4183 0.01367 0.00559 -0.0181 0.5488 1.0000
2.250 0.4359 0.01390 0.00555 -0.0163 0.5127 1.0000
2.500 0.4543 0.01424 0.00562 -0.0146 0.4819 1.0000
2.750 0.4735 0.01465 0.00581 -0.0131 0.4547 1.0000
3.000 0.4936 0.01514 0.00609 -0.0118 0.4319 1.0000
3.250 0.5145 0.01567 0.00645 -0.0107 0.4117 1.0000
3.500 0.5360 0.01621 0.00683 -0.0096 0.3942 1.0000
3.750 0.5581 0.01675 0.00728 -0.0087 0.3785 1.0000
4.000 0.5807 0.01727 0.00773 -0.0078 0.3646 1.0000
4.250 0.6037 0.01780 0.00825 -0.0070 0.3527 1.0000
4.500 0.6274 0.01838 0.00877 -0.0064 0.3432 1.0000
4.750 0.6514 0.01894 0.00933 -0.0057 0.3345 1.0000
5.000 0.6755 0.01958 0.01002 -0.0052 0.3269 1.0000
5.250 0.7000 0.02018 0.01061 -0.0047 0.3199 1.0000
5.500 0.7241 0.02087 0.01137 -0.0042 0.3131 1.0000
5.750 0.7485 0.02148 0.01205 -0.0037 0.3063 1.0000
6.000 0.7726 0.02217 0.01279 -0.0032 0.2995 1.0000
6.250 0.7965 0.02265 0.01330 -0.0026 0.2908 1.0000
6.500 0.8194 0.02317 0.01394 -0.0019 0.2812 1.0000
6.750 0.8439 0.02367 0.01434 -0.0015 0.2728 1.0000
7.000 0.8664 0.02430 0.01521 -0.0008 0.2647 1.0000
7.250 0.8914 0.02502 0.01587 -0.0005 0.2583 1.0000
7.500 0.9129 0.02578 0.01697 0.0002 0.2507 1.0000
7.750 0.9379 0.02646 0.01757 0.0006 0.2436 1.0000
8.000 0.9585 0.02684 0.01818 0.0015 0.2328 1.0000
8.250 0.9794 0.02709 0.01854 0.0023 0.2209 1.0000
8.500 1.0010 0.02738 0.01890 0.0031 0.2105 1.0000
8.750 1.0236 0.02746 0.01893 0.0038 0.2002 1.0000
9.000 1.0427 0.02750 0.01911 0.0048 0.1885 1.0000
9.250 1.0611 0.02792 0.01975 0.0059 0.1780 1.0000
9.500 1.0811 0.02841 0.02032 0.0067 0.1698 1.0000
9.750 1.1000 0.02881 0.02088 0.0077 0.1613 1.0000
10.000 1.1164 0.02921 0.02151 0.0089 0.1517 1.0000
10.250 1.1328 0.02939 0.02180 0.0100 0.1425 1.0000
10.500 1.1486 0.02982 0.02247 0.0113 0.1335 1.0000
10.750 1.1638 0.03048 0.02341 0.0125 0.1242 1.0000
11.000 1.1768 0.03097 0.02409 0.0139 0.1102 1.0000
11.250 1.1841 0.03192 0.02501 0.0156 0.0939 1.0000
11.500 1.1813 0.03372 0.02681 0.0180 0.0795 1.0000
11.750 1.1710 0.03613 0.02920 0.0203 0.0710 1.0000
12.000 1.1609 0.03900 0.03219 0.0217 0.0626 1.0000
12.250 1.1463 0.04259 0.03581 0.0219 0.0585 1.0000
12.500 1.1352 0.04640 0.03981 0.0214 0.0544 1.0000
12.750 1.1217 0.05083 0.04437 0.0200 0.0520 1.0000
13.000 1.1065 0.05589 0.04954 0.0178 0.0504 1.0000
13.250 1.0915 0.06131 0.05504 0.0152 0.0494 1.0000
13.500 1.0774 0.06690 0.06072 0.0125 0.0478 1.0000
13.750 1.0669 0.07213 0.06610 0.0101 0.0467 1.0000
14.000 1.0570 0.07732 0.07143 0.0078 0.0456 1.0000
14.250 1.0466 0.08271 0.07693 0.0054 0.0443 1.0000
14.500 1.0377 0.08790 0.08223 0.0031 0.0433 1.0000
14.750 1.0298 0.09304 0.08747 0.0008 0.0423 1.0000
15.000 1.0236 0.09800 0.09251 -0.0014 0.0415 1.0000
15.250 1.0196 0.10255 0.09711 -0.0032 0.0406 1.0000
15.500 1.0213 0.10576 0.10032 -0.0039 0.0394 1.0000
15.750 1.0103 0.11218 0.10687 -0.0071 0.0393 1.0000
16.000 0.9949 0.11980 0.11463 -0.0112 0.0393 1.0000
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Polar data table (+)
Polar graphs
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