S3025 9.38% (s3025-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3025 9.38% (s3025-il) Reynolds number: 50,000 Max Cl/Cd: 33.87 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3025-il-50000.txt Download as CSV file: xf-s3025-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S3025 9.38%
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3426 0.10175 0.09524 -0.0253 1.0000 0.2106
-7.750 -0.3379 0.09838 0.09194 -0.0246 1.0000 0.2168
-7.500 -0.3465 0.09700 0.09070 -0.0240 1.0000 0.2259
-7.250 -0.3377 0.09328 0.08705 -0.0227 1.0000 0.2335
-7.000 -0.3585 0.09294 0.08691 -0.0214 1.0000 0.2412
-6.750 -0.3465 0.08900 0.08300 -0.0195 1.0000 0.2518
-6.500 -0.3672 0.08799 0.08222 -0.0187 1.0000 0.2587
-6.250 -0.3697 0.08590 0.08021 -0.0168 1.0000 0.2708
-6.000 -0.3643 0.08271 0.07711 -0.0139 1.0000 0.2821
-5.750 -0.3711 0.08063 0.07515 -0.0118 1.0000 0.2926
-5.500 -0.3826 0.07893 0.07358 -0.0097 1.0000 0.3051
-5.000 -0.3983 0.07528 0.07014 -0.0048 1.0000 0.3340
-4.750 -0.4010 0.07308 0.06802 -0.0013 1.0000 0.3505
-4.500 -0.4035 0.07099 0.06601 0.0022 1.0000 0.3692
-3.500 -0.2931 0.04556 0.03853 -0.0413 1.0000 0.1369
-3.250 -0.2646 0.04146 0.03377 -0.0433 1.0000 0.1227
-3.000 -0.2407 0.03861 0.03057 -0.0439 1.0000 0.1199
-2.750 -0.2144 0.03589 0.02729 -0.0445 1.0000 0.1161
-2.500 -0.1872 0.03352 0.02425 -0.0447 1.0000 0.1130
-2.250 -0.1627 0.03175 0.02206 -0.0445 1.0000 0.1137
-2.000 -0.1399 0.03049 0.02055 -0.0440 1.0000 0.1187
-1.750 -0.1163 0.02933 0.01912 -0.0436 1.0000 0.1287
-1.500 -0.0937 0.02832 0.01793 -0.0428 1.0000 0.1416
-1.250 -0.0702 0.02741 0.01709 -0.0423 1.0000 0.1748
-1.000 -0.0383 0.02521 0.01598 -0.0428 1.0000 0.3632
-0.750 -0.0194 0.02279 0.01520 -0.0399 1.0000 1.0000
-0.500 0.0218 0.02379 0.01551 -0.0437 0.9907 1.0000
-0.250 0.0661 0.02485 0.01603 -0.0479 0.9787 1.0000
0.000 0.1077 0.02584 0.01660 -0.0517 0.9666 1.0000
0.250 0.1484 0.02681 0.01723 -0.0553 0.9546 1.0000
0.500 0.1893 0.02777 0.01788 -0.0588 0.9425 1.0000
0.750 0.2303 0.02868 0.01855 -0.0622 0.9302 1.0000
1.000 0.2647 0.02948 0.01917 -0.0644 0.9171 1.0000
1.250 0.2980 0.03029 0.01981 -0.0663 0.9039 1.0000
1.500 0.3313 0.03110 0.02049 -0.0682 0.8906 1.0000
1.750 0.3643 0.03190 0.02120 -0.0699 0.8770 1.0000
2.000 0.3968 0.03270 0.02192 -0.0715 0.8634 1.0000
2.250 0.4294 0.03350 0.02266 -0.0729 0.8494 1.0000
2.500 0.4616 0.03427 0.02340 -0.0742 0.8354 1.0000
2.750 0.4935 0.03504 0.02416 -0.0754 0.8211 1.0000
3.000 0.5253 0.03578 0.02489 -0.0764 0.8065 1.0000
3.250 0.5569 0.03648 0.02562 -0.0772 0.7916 1.0000
3.500 0.5881 0.03717 0.02634 -0.0779 0.7766 1.0000
3.750 0.6195 0.03781 0.02706 -0.0785 0.7614 1.0000
4.000 0.6521 0.03835 0.02767 -0.0791 0.7459 1.0000
4.250 0.6858 0.03879 0.02820 -0.0796 0.7304 1.0000
4.500 0.7211 0.03908 0.02863 -0.0800 0.7149 1.0000
4.750 0.7568 0.03922 0.02889 -0.0802 0.6994 1.0000
5.000 0.7927 0.03919 0.02899 -0.0801 0.6838 1.0000
5.250 0.8301 0.03892 0.02887 -0.0799 0.6681 1.0000
5.500 0.8538 0.03938 0.02950 -0.0785 0.6503 1.0000
5.750 0.8755 0.03992 0.03018 -0.0769 0.6314 1.0000
6.000 0.9100 0.03951 0.02994 -0.0760 0.6139 1.0000
6.250 0.9506 0.03848 0.02913 -0.0750 0.5966 1.0000
6.500 0.9842 0.03789 0.02870 -0.0736 0.5776 1.0000
6.750 1.0075 0.03801 0.02899 -0.0717 0.5564 1.0000
7.000 1.0548 0.03616 0.02731 -0.0708 0.5364 1.0000
7.250 1.0720 0.03670 0.02802 -0.0685 0.5127 1.0000
7.500 1.1041 0.03602 0.02745 -0.0668 0.4889 1.0000
7.750 1.1386 0.03515 0.02664 -0.0653 0.4631 1.0000
8.000 1.1646 0.03501 0.02656 -0.0634 0.4358 1.0000
8.250 1.1863 0.03532 0.02693 -0.0613 0.4079 1.0000
8.500 1.2078 0.03574 0.02736 -0.0592 0.3793 1.0000
8.750 1.2289 0.03628 0.02790 -0.0571 0.3500 1.0000
9.000 1.2487 0.03705 0.02857 -0.0551 0.3201 1.0000
9.250 1.2631 0.03822 0.02973 -0.0526 0.2908 1.0000
9.500 1.2743 0.03959 0.03109 -0.0499 0.2613 1.0000
9.750 1.2806 0.04097 0.03244 -0.0467 0.2310 1.0000
10.000 1.2800 0.04207 0.03343 -0.0430 0.2005 1.0000
10.250 1.2760 0.04349 0.03470 -0.0392 0.1729 1.0000
10.500 1.2741 0.04571 0.03682 -0.0358 0.1476 1.0000
10.750 1.2822 0.04863 0.03943 -0.0336 0.1247 1.0000
11.000 1.2875 0.05178 0.04269 -0.0314 0.1111 1.0000
11.250 1.2859 0.05479 0.04604 -0.0286 0.1031 1.0000
11.500 1.2920 0.05861 0.05005 -0.0269 0.0970 1.0000
11.750 1.2836 0.06241 0.05427 -0.0243 0.0946 1.0000
12.000 1.2737 0.06635 0.05854 -0.0221 0.0928 1.0000
12.250 1.2611 0.07051 0.06299 -0.0205 0.0915 1.0000
12.500 1.2420 0.07514 0.06791 -0.0196 0.0911 1.0000
12.750 1.2125 0.08072 0.07380 -0.0199 0.0923 1.0000
13.000 1.1796 0.08738 0.08071 -0.0219 0.0938 1.0000
13.250 1.1469 0.09504 0.08856 -0.0252 0.0955 1.0000
13.500 1.1175 0.10342 0.09705 -0.0295 0.0972 1.0000
13.750 1.0918 0.11232 0.10601 -0.0341 0.0986 1.0000
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Polar data table (+)
Polar graphs
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