SA7025 (sa7025-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7025 (sa7025-il) Reynolds number: 100,000 Max Cl/Cd: 60.57 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7025-il-100000.txt Download as CSV file: xf-sa7025-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SA7025
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3470 0.09400 0.08940 -0.0307 1.0000 0.0779
-7.500 -0.3554 0.09224 0.08774 -0.0297 1.0000 0.0801
-7.250 -0.3708 0.09119 0.08680 -0.0280 1.0000 0.0816
-7.000 -0.3873 0.09008 0.08580 -0.0284 1.0000 0.0827
-6.750 -0.3993 0.08854 0.08433 -0.0332 1.0000 0.0835
-6.500 -0.4021 0.08472 0.08057 -0.0337 1.0000 0.0844
-6.250 -0.3965 0.08154 0.07744 -0.0260 1.0000 0.0868
-6.000 -0.3957 0.07912 0.07506 -0.0245 1.0000 0.0895
-5.750 -0.3952 0.07641 0.07237 -0.0256 1.0000 0.0933
-5.500 -0.3877 0.07212 0.06794 -0.0372 1.0000 0.0981
-5.250 -0.3863 0.06928 0.06523 -0.0313 1.0000 0.1001
-5.000 -0.3803 0.06679 0.06277 -0.0298 1.0000 0.1040
-4.750 -0.3631 0.06223 0.05802 -0.0373 1.0000 0.1129
-4.500 -0.3427 0.05985 0.05533 -0.0419 1.0000 0.1251
-4.250 -0.3373 0.05595 0.05164 -0.0389 1.0000 0.1275
-4.000 -0.3250 0.05355 0.04925 -0.0379 1.0000 0.1343
-3.750 -0.3071 0.05036 0.04593 -0.0396 1.0000 0.1454
-3.500 -0.2875 0.04751 0.04298 -0.0411 1.0000 0.1589
-3.250 -0.2635 0.04484 0.04008 -0.0439 1.0000 0.1829
-3.000 -0.2484 0.04274 0.03805 -0.0427 1.0000 0.2005
-2.750 -0.1639 0.03106 0.02438 -0.0541 1.0000 0.0795
-2.500 -0.1305 0.02777 0.02032 -0.0546 1.0000 0.0665
-2.250 -0.0896 0.02510 0.01698 -0.0566 0.9969 0.0606
-2.000 -0.0451 0.02338 0.01473 -0.0591 0.9914 0.0588
-1.750 -0.0020 0.02204 0.01320 -0.0618 0.9853 0.0606
-1.500 0.0390 0.02114 0.01224 -0.0642 0.9782 0.0656
-1.250 0.0829 0.02038 0.01150 -0.0673 0.9715 0.0850
-1.000 0.1166 0.01737 0.01104 -0.0684 0.9669 0.6592
-0.750 0.1631 0.01701 0.01080 -0.0714 0.9582 1.0000
-0.500 0.2024 0.01732 0.01077 -0.0739 0.9474 1.0000
-0.250 0.2431 0.01762 0.01080 -0.0766 0.9372 1.0000
0.000 0.2911 0.01788 0.01081 -0.0806 0.9292 1.0000
0.250 0.3275 0.01804 0.01081 -0.0823 0.9175 1.0000
0.500 0.3651 0.01817 0.01081 -0.0842 0.9060 1.0000
0.750 0.4047 0.01824 0.01076 -0.0863 0.8952 1.0000
1.000 0.4557 0.01811 0.01054 -0.0903 0.8880 1.0000
1.250 0.4922 0.01805 0.01043 -0.0917 0.8759 1.0000
1.500 0.5282 0.01794 0.01029 -0.0928 0.8641 1.0000
1.750 0.5643 0.01776 0.01010 -0.0937 0.8526 1.0000
2.000 0.6011 0.01749 0.00982 -0.0946 0.8415 1.0000
2.250 0.6418 0.01702 0.00935 -0.0959 0.8326 1.0000
2.500 0.6736 0.01672 0.00909 -0.0958 0.8192 1.0000
2.750 0.7051 0.01639 0.00878 -0.0954 0.8053 1.0000
3.000 0.7333 0.01617 0.00858 -0.0946 0.7890 1.0000
3.250 0.7616 0.01595 0.00839 -0.0938 0.7719 1.0000
3.500 0.7908 0.01570 0.00820 -0.0930 0.7545 1.0000
3.750 0.8207 0.01545 0.00795 -0.0924 0.7368 1.0000
4.000 0.8465 0.01542 0.00793 -0.0912 0.7146 1.0000
4.250 0.8742 0.01537 0.00785 -0.0903 0.6927 1.0000
4.500 0.9002 0.01544 0.00795 -0.0892 0.6684 1.0000
4.750 0.9250 0.01561 0.00811 -0.0881 0.6424 1.0000
5.000 0.9495 0.01584 0.00831 -0.0869 0.6155 1.0000
5.250 0.9735 0.01612 0.00856 -0.0857 0.5875 1.0000
5.500 0.9969 0.01646 0.00890 -0.0844 0.5586 1.0000
5.750 1.0197 0.01684 0.00924 -0.0831 0.5290 1.0000
6.000 1.0417 0.01729 0.00965 -0.0817 0.4985 1.0000
6.250 1.0629 0.01779 0.01015 -0.0803 0.4668 1.0000
6.500 1.0836 0.01833 0.01066 -0.0788 0.4346 1.0000
6.750 1.1036 0.01894 0.01123 -0.0773 0.4024 1.0000
7.000 1.1219 0.01957 0.01188 -0.0756 0.3670 1.0000
7.250 1.1395 0.02030 0.01252 -0.0738 0.3324 1.0000
7.500 1.1558 0.02109 0.01330 -0.0719 0.2955 1.0000
7.750 1.1704 0.02198 0.01414 -0.0699 0.2578 1.0000
8.000 1.1823 0.02294 0.01500 -0.0676 0.2155 1.0000
8.250 1.1914 0.02413 0.01597 -0.0652 0.1685 1.0000
8.500 1.1978 0.02585 0.01736 -0.0627 0.1086 1.0000
8.750 1.1948 0.02884 0.01992 -0.0587 0.0630 1.0000
9.000 1.1975 0.03132 0.02239 -0.0552 0.0488 1.0000
9.250 1.2020 0.03378 0.02478 -0.0522 0.0426 1.0000
9.500 1.2190 0.03632 0.02749 -0.0504 0.0388 1.0000
9.750 1.2408 0.03907 0.03042 -0.0495 0.0361 1.0000
10.000 1.2608 0.04200 0.03352 -0.0486 0.0340 1.0000
10.250 1.2813 0.04672 0.03837 -0.0485 0.0317 1.0000
10.500 1.2865 0.04970 0.04177 -0.0460 0.0307 1.0000
10.750 1.2884 0.05264 0.04511 -0.0433 0.0302 1.0000
11.000 1.2845 0.05584 0.04869 -0.0403 0.0299 1.0000
11.250 1.2773 0.05942 0.05261 -0.0375 0.0300 1.0000
11.500 1.2661 0.06315 0.05666 -0.0350 0.0302 1.0000
11.750 1.2524 0.06709 0.06089 -0.0331 0.0303 1.0000
12.000 1.2363 0.07141 0.06548 -0.0319 0.0305 1.0000
12.250 1.2194 0.07609 0.07040 -0.0315 0.0307 1.0000
12.500 1.2014 0.08128 0.07581 -0.0321 0.0309 1.0000
12.750 1.1819 0.08697 0.08170 -0.0335 0.0311 1.0000
13.000 1.1638 0.09335 0.08824 -0.0357 0.0313 1.0000
13.250 1.1471 0.09935 0.09446 -0.0386 0.0316 1.0000
13.500 1.1282 0.10575 0.10105 -0.0428 0.0319 1.0000
13.750 1.1055 0.11379 0.10929 -0.0490 0.0323 1.0000
14.000 0.8807 0.13002 0.12619 -0.0568 0.0408 1.0000
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Polar data table (+)
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