S3025 9.38% (s3025-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3025 9.38% (s3025-il) Reynolds number: 100,000 Max Cl/Cd: 56.96 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3025-il-100000.txt Download as CSV file: xf-s3025-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3704 0.12528 0.12012 -0.0279 1.0000 0.0676
-10.250 -0.3768 0.12401 0.11893 -0.0312 1.0000 0.0681
-10.000 -0.3823 0.12230 0.11730 -0.0341 1.0000 0.0684
-9.750 -0.3542 0.11402 0.10898 -0.0295 1.0000 0.0708
-9.500 -0.3455 0.11075 0.10571 -0.0292 1.0000 0.0730
-9.250 -0.3409 0.10783 0.10283 -0.0296 1.0000 0.0755
-9.000 -0.3397 0.10510 0.10016 -0.0307 1.0000 0.0784
-8.750 -0.2595 0.09158 0.08714 -0.0343 1.0000 0.0855
-8.500 -0.2557 0.08854 0.08414 -0.0337 1.0000 0.0884
-8.250 -0.2574 0.08570 0.08135 -0.0336 1.0000 0.0912
-8.000 -0.3419 0.09358 0.08893 -0.0332 1.0000 0.0852
-7.750 -0.3380 0.09094 0.08635 -0.0323 1.0000 0.0878
-7.500 -0.3416 0.08862 0.08412 -0.0319 1.0000 0.0906
-7.250 -0.3531 0.08680 0.08242 -0.0313 1.0000 0.0928
-7.000 -0.3705 0.08508 0.08084 -0.0337 1.0000 0.0949
-6.750 -0.3923 0.08336 0.07914 -0.0403 1.0000 0.0960
-6.500 -0.3885 0.07923 0.07515 -0.0350 1.0000 0.0973
-6.250 -0.3862 0.07701 0.07301 -0.0301 1.0000 0.0994
-6.000 -0.3909 0.07509 0.07115 -0.0277 1.0000 0.1020
-5.750 -0.3975 0.07308 0.06919 -0.0269 1.0000 0.1049
-5.500 -0.4058 0.06981 0.06571 -0.0350 1.0000 0.1109
-5.250 -0.4050 0.06714 0.06320 -0.0305 1.0000 0.1125
-5.000 -0.4004 0.06504 0.06114 -0.0283 0.9994 0.1156
-4.750 -0.3613 0.05963 0.05552 -0.0378 0.9917 0.1279
-4.500 -0.3228 0.05517 0.05089 -0.0448 0.9846 0.1423
-4.250 -0.2815 0.05242 0.04770 -0.0525 0.9751 0.1682
-3.750 -0.1886 0.03638 0.02989 -0.0635 0.9626 0.0814
-3.500 -0.1450 0.03107 0.02394 -0.0666 0.9585 0.0662
-3.250 -0.1111 0.02805 0.02042 -0.0678 0.9500 0.0618
-3.000 -0.0661 0.02540 0.01711 -0.0703 0.9451 0.0597
-2.750 -0.0318 0.02379 0.01521 -0.0712 0.9363 0.0608
-2.500 0.0136 0.02261 0.01373 -0.0739 0.9308 0.0683
-2.250 0.0452 0.02119 0.01243 -0.0746 0.9216 0.0776
-2.000 0.0887 0.01960 0.01105 -0.0771 0.9165 0.1194
-1.750 0.1110 0.01698 0.01062 -0.0764 0.9079 0.5611
-1.500 0.1819 0.01589 0.01011 -0.0828 0.9061 1.0000
-1.250 0.2270 0.01582 0.00965 -0.0861 0.8994 1.0000
-1.000 0.2634 0.01580 0.00936 -0.0876 0.8899 1.0000
-0.750 0.2969 0.01584 0.00916 -0.0886 0.8801 1.0000
-0.500 0.3389 0.01569 0.00879 -0.0909 0.8733 1.0000
-0.250 0.3669 0.01579 0.00873 -0.0908 0.8621 1.0000
0.000 0.3983 0.01581 0.00860 -0.0912 0.8523 1.0000
0.250 0.4340 0.01570 0.00835 -0.0922 0.8441 1.0000
0.500 0.4597 0.01585 0.00839 -0.0916 0.8324 1.0000
0.750 0.4871 0.01595 0.00839 -0.0912 0.8216 1.0000
1.000 0.5187 0.01590 0.00824 -0.0913 0.8125 1.0000
1.250 0.5450 0.01601 0.00827 -0.0906 0.8011 1.0000
1.500 0.5698 0.01618 0.00837 -0.0897 0.7891 1.0000
1.750 0.5958 0.01631 0.00846 -0.0890 0.7777 1.0000
2.000 0.6235 0.01638 0.00846 -0.0884 0.7670 1.0000
2.250 0.6509 0.01644 0.00846 -0.0878 0.7560 1.0000
2.500 0.6751 0.01663 0.00863 -0.0868 0.7433 1.0000
2.750 0.6999 0.01681 0.00881 -0.0859 0.7307 1.0000
3.000 0.7252 0.01698 0.00895 -0.0851 0.7183 1.0000
3.250 0.7510 0.01711 0.00906 -0.0843 0.7060 1.0000
3.500 0.7773 0.01722 0.00915 -0.0835 0.6937 1.0000
3.750 0.8041 0.01731 0.00923 -0.0828 0.6814 1.0000
4.000 0.8294 0.01744 0.00937 -0.0819 0.6677 1.0000
4.250 0.8543 0.01759 0.00952 -0.0809 0.6534 1.0000
4.500 0.8794 0.01771 0.00969 -0.0800 0.6387 1.0000
4.750 0.9047 0.01783 0.00981 -0.0791 0.6236 1.0000
5.000 0.9283 0.01799 0.01001 -0.0779 0.6068 1.0000
5.250 0.9521 0.01814 0.01021 -0.0768 0.5893 1.0000
5.500 0.9762 0.01826 0.01039 -0.0757 0.5714 1.0000
5.750 1.0009 0.01837 0.01050 -0.0747 0.5533 1.0000
6.000 1.0247 0.01852 0.01067 -0.0735 0.5339 1.0000
6.250 1.0470 0.01872 0.01092 -0.0722 0.5125 1.0000
6.500 1.0704 0.01891 0.01111 -0.0710 0.4914 1.0000
6.750 1.0916 0.01919 0.01143 -0.0696 0.4676 1.0000
7.000 1.1125 0.01953 0.01178 -0.0681 0.4433 1.0000
7.250 1.1333 0.01992 0.01216 -0.0667 0.4188 1.0000
7.500 1.1527 0.02040 0.01262 -0.0651 0.3930 1.0000
7.750 1.1708 0.02098 0.01321 -0.0634 0.3662 1.0000
8.000 1.1881 0.02164 0.01386 -0.0616 0.3393 1.0000
8.250 1.2043 0.02239 0.01458 -0.0598 0.3124 1.0000
8.500 1.2189 0.02321 0.01538 -0.0577 0.2853 1.0000
8.750 1.2307 0.02403 0.01616 -0.0554 0.2574 1.0000
9.000 1.2403 0.02488 0.01698 -0.0529 0.2294 1.0000
9.250 1.2480 0.02580 0.01788 -0.0503 0.2023 1.0000
9.500 1.2540 0.02685 0.01890 -0.0475 0.1757 1.0000
9.750 1.2569 0.02813 0.02010 -0.0444 0.1517 1.0000
10.000 1.2545 0.02976 0.02164 -0.0408 0.1249 1.0000
10.250 1.2468 0.03209 0.02383 -0.0369 0.0959 1.0000
10.500 1.2388 0.03475 0.02636 -0.0335 0.0768 1.0000
10.750 1.2372 0.03721 0.02878 -0.0310 0.0658 1.0000
11.000 1.2403 0.03959 0.03119 -0.0289 0.0588 1.0000
11.250 1.2449 0.04185 0.03341 -0.0273 0.0536 1.0000
11.500 1.2603 0.04429 0.03594 -0.0258 0.0500 1.0000
11.750 1.2761 0.04668 0.03854 -0.0246 0.0473 1.0000
12.000 1.2917 0.04926 0.04128 -0.0235 0.0452 1.0000
12.250 1.3093 0.05226 0.04436 -0.0228 0.0432 1.0000
12.500 1.3214 0.05654 0.04885 -0.0221 0.0416 1.0000
12.750 1.3145 0.05950 0.05217 -0.0204 0.0410 1.0000
13.000 1.3058 0.06302 0.05606 -0.0191 0.0405 1.0000
13.250 1.2945 0.06694 0.06030 -0.0183 0.0401 1.0000
13.500 1.2811 0.07132 0.06498 -0.0181 0.0400 1.0000
13.750 1.2652 0.07622 0.07018 -0.0185 0.0401 1.0000
14.000 1.2472 0.08153 0.07575 -0.0196 0.0401 1.0000
14.250 1.2281 0.08731 0.08177 -0.0214 0.0404 1.0000
14.500 1.2065 0.09371 0.08840 -0.0241 0.0406 1.0000
14.750 1.1840 0.10074 0.09563 -0.0275 0.0408 1.0000
15.000 1.1620 0.10822 0.10325 -0.0316 0.0412 1.0000
15.250 1.1395 0.11645 0.11164 -0.0365 0.0415 1.0000
15.500 1.1189 0.12513 0.12042 -0.0416 0.0419 1.0000
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Polar data table (+)
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