SG6040 (sg6040-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6040 (sg6040-il) Reynolds number: 100,000 Max Cl/Cd: 50.91 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6040-il-100000-n5.txt Download as CSV file: xf-sg6040-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SG6040
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5328 0.09221 0.08646 -0.0668 1.0000 0.0287
-13.250 -0.5779 0.08007 0.07417 -0.0741 1.0000 0.0283
-13.000 -0.6099 0.07220 0.06614 -0.0785 1.0000 0.0280
-12.750 -0.6375 0.06610 0.05987 -0.0811 1.0000 0.0278
-12.500 -0.6609 0.06129 0.05488 -0.0823 1.0000 0.0278
-12.250 -0.6804 0.05740 0.05083 -0.0824 1.0000 0.0277
-12.000 -0.6992 0.05404 0.04730 -0.0816 1.0000 0.0278
-11.750 -0.7164 0.05122 0.04432 -0.0800 1.0000 0.0280
-11.500 -0.7317 0.04894 0.04190 -0.0777 1.0000 0.0280
-11.250 -0.7490 0.04703 0.03986 -0.0744 1.0000 0.0283
-11.000 -0.7674 0.04548 0.03819 -0.0703 1.0000 0.0284
-10.750 -0.7895 0.04438 0.03698 -0.0651 1.0000 0.0286
-10.500 -0.7993 0.04296 0.03540 -0.0616 0.9989 0.0288
-10.250 -0.7784 0.04081 0.03307 -0.0636 0.9933 0.0297
-10.000 -0.7566 0.03916 0.03133 -0.0651 0.9870 0.0309
-9.750 -0.7322 0.03736 0.02934 -0.0667 0.9817 0.0320
-9.500 -0.7099 0.03564 0.02739 -0.0675 0.9752 0.0330
-9.250 -0.6819 0.03397 0.02548 -0.0690 0.9708 0.0342
-9.000 -0.6625 0.03262 0.02413 -0.0691 0.9629 0.0352
-8.750 -0.6349 0.03128 0.02273 -0.0705 0.9580 0.0368
-8.500 -0.6150 0.03011 0.02143 -0.0703 0.9500 0.0387
-8.250 -0.5882 0.02891 0.02019 -0.0715 0.9447 0.0418
-8.000 -0.5665 0.02793 0.01912 -0.0714 0.9374 0.0455
-7.750 -0.5410 0.02689 0.01808 -0.0722 0.9314 0.0506
-7.500 -0.5103 0.02581 0.01698 -0.0738 0.9277 0.0588
-7.250 -0.4926 0.02504 0.01622 -0.0727 0.9187 0.0682
-7.000 -0.4617 0.02425 0.01537 -0.0740 0.9143 0.0840
-6.750 -0.4355 0.02353 0.01471 -0.0745 0.9086 0.0998
-6.500 -0.4109 0.02294 0.01416 -0.0747 0.9016 0.1174
-6.250 -0.3780 0.02230 0.01351 -0.0763 0.8977 0.1392
-6.000 -0.3531 0.02170 0.01296 -0.0764 0.8913 0.1572
-5.750 -0.3281 0.02107 0.01240 -0.0764 0.8845 0.1772
-5.500 -0.2965 0.02036 0.01176 -0.0777 0.8804 0.2045
-5.250 -0.2753 0.01976 0.01127 -0.0770 0.8726 0.2345
-5.000 -0.2493 0.01900 0.01072 -0.0773 0.8665 0.2819
-4.750 -0.2190 0.01816 0.01021 -0.0783 0.8625 0.3550
-4.500 -0.2013 0.01782 0.01022 -0.0766 0.8534 0.4273
-4.000 -0.1394 0.01773 0.01025 -0.0770 0.8433 0.5318
-3.750 -0.1159 0.01782 0.01025 -0.0761 0.8349 0.5573
-3.500 -0.0830 0.01784 0.01017 -0.0766 0.8301 0.5795
-3.250 -0.0568 0.01795 0.01019 -0.0760 0.8228 0.5974
-3.000 -0.0291 0.01804 0.01021 -0.0756 0.8160 0.6138
-2.750 0.0043 0.01809 0.01017 -0.0762 0.8115 0.6300
-2.500 0.0257 0.01826 0.01028 -0.0747 0.8026 0.6443
-2.250 0.0558 0.01832 0.01025 -0.0747 0.7967 0.6593
-2.000 0.0822 0.01845 0.01037 -0.0739 0.7900 0.6698
-1.750 0.1077 0.01849 0.01034 -0.0732 0.7822 0.6799
-1.500 0.1403 0.01842 0.01019 -0.0737 0.7772 0.6885
-1.250 0.1619 0.01845 0.01017 -0.0726 0.7680 0.6961
-1.000 0.1922 0.01838 0.01004 -0.0728 0.7620 0.7019
-0.750 0.2176 0.01834 0.00993 -0.0725 0.7540 0.7086
-0.500 0.2457 0.01827 0.00979 -0.0725 0.7468 0.7138
-0.250 0.2742 0.01821 0.00969 -0.0724 0.7402 0.7185
0.000 0.2990 0.01820 0.00964 -0.0720 0.7318 0.7241
0.250 0.3321 0.01806 0.00940 -0.0730 0.7262 0.7295
0.500 0.3530 0.01812 0.00950 -0.0717 0.7168 0.7337
0.750 0.3837 0.01803 0.00935 -0.0721 0.7105 0.7384
1.000 0.4078 0.01807 0.00937 -0.0717 0.7019 0.7441
1.250 0.4368 0.01801 0.00928 -0.0718 0.6949 0.7484
1.500 0.4613 0.01805 0.00933 -0.0712 0.6867 0.7528
1.750 0.4891 0.01804 0.00930 -0.0712 0.6792 0.7581
2.000 0.5163 0.01806 0.00929 -0.0712 0.6714 0.7636
2.250 0.5416 0.01808 0.00934 -0.0707 0.6633 0.7677
2.500 0.5686 0.01810 0.00936 -0.0705 0.6559 0.7729
2.750 0.5942 0.01816 0.00943 -0.0703 0.6471 0.7790
3.000 0.6214 0.01818 0.00946 -0.0701 0.6399 0.7837
3.250 0.6448 0.01828 0.00960 -0.0693 0.6309 0.7891
3.500 0.6733 0.01832 0.00962 -0.0695 0.6237 0.7955
3.750 0.6957 0.01844 0.00982 -0.0685 0.6146 0.8013
4.000 0.7236 0.01848 0.00987 -0.0685 0.6074 0.8075
4.250 0.7466 0.01864 0.01009 -0.0678 0.5981 0.8145
4.500 0.7733 0.01869 0.01018 -0.0675 0.5908 0.8208
4.750 0.7951 0.01887 0.01044 -0.0665 0.5815 0.8292
5.000 0.8211 0.01894 0.01053 -0.0661 0.5739 0.8367
5.250 0.8423 0.01912 0.01082 -0.0650 0.5642 0.8462
5.500 0.8658 0.01921 0.01096 -0.0641 0.5554 0.8549
5.750 0.8876 0.01933 0.01114 -0.0630 0.5451 0.8658
6.000 0.9069 0.01946 0.01138 -0.0614 0.5343 0.8788
6.250 0.9291 0.01950 0.01146 -0.0602 0.5235 0.8936
6.500 0.9493 0.01961 0.01166 -0.0588 0.5113 0.9133
6.750 0.9735 0.01976 0.01192 -0.0584 0.4980 0.9410
7.000 1.0021 0.01992 0.01215 -0.0591 0.4838 1.0000
7.250 1.0234 0.02021 0.01242 -0.0583 0.4698 1.0000
7.500 1.0435 0.02051 0.01272 -0.0574 0.4555 1.0000
7.750 1.0619 0.02086 0.01305 -0.0561 0.4408 1.0000
8.000 1.0777 0.02122 0.01341 -0.0543 0.4258 1.0000
8.250 1.0915 0.02165 0.01383 -0.0523 0.4101 1.0000
8.500 1.1036 0.02216 0.01435 -0.0500 0.3931 1.0000
8.750 1.1143 0.02274 0.01493 -0.0477 0.3749 1.0000
9.000 1.1238 0.02342 0.01559 -0.0453 0.3549 1.0000
9.250 1.1319 0.02419 0.01631 -0.0428 0.3339 1.0000
9.500 1.1384 0.02510 0.01716 -0.0403 0.3119 1.0000
9.750 1.1437 0.02614 0.01815 -0.0378 0.2883 1.0000
10.000 1.1471 0.02738 0.01929 -0.0353 0.2651 1.0000
10.250 1.1496 0.02877 0.02059 -0.0330 0.2408 1.0000
10.500 1.1502 0.03038 0.02209 -0.0307 0.2191 1.0000
10.750 1.1514 0.03208 0.02373 -0.0287 0.1990 1.0000
11.000 1.1523 0.03392 0.02550 -0.0269 0.1814 1.0000
11.250 1.1530 0.03587 0.02740 -0.0253 0.1657 1.0000
11.500 1.1539 0.03789 0.02940 -0.0239 0.1522 1.0000
11.750 1.1548 0.04001 0.03149 -0.0226 0.1406 1.0000
12.000 1.1546 0.04230 0.03375 -0.0215 0.1306 1.0000
12.250 1.1571 0.04445 0.03594 -0.0206 0.1209 1.0000
12.500 1.1585 0.04677 0.03829 -0.0199 0.1131 1.0000
12.750 1.1594 0.04921 0.04075 -0.0193 0.1061 1.0000
13.000 1.1618 0.05159 0.04317 -0.0187 0.0999 1.0000
13.250 1.1634 0.05412 0.04575 -0.0184 0.0942 1.0000
13.500 1.1650 0.05670 0.04835 -0.0181 0.0894 1.0000
13.750 1.1687 0.05914 0.05087 -0.0179 0.0846 1.0000
14.000 1.1697 0.06190 0.05366 -0.0179 0.0808 1.0000
14.250 1.1739 0.06439 0.05622 -0.0178 0.0771 1.0000
14.500 1.1779 0.06694 0.05887 -0.0178 0.0735 1.0000
14.750 1.1804 0.06970 0.06167 -0.0180 0.0706 1.0000
15.000 1.1845 0.07230 0.06429 -0.0181 0.0680 1.0000
15.250 1.1894 0.07490 0.06705 -0.0183 0.0652 1.0000
15.500 1.1930 0.07769 0.06992 -0.0187 0.0627 1.0000
15.750 1.1961 0.08052 0.07280 -0.0192 0.0606 1.0000
16.000 1.2008 0.08317 0.07548 -0.0195 0.0587 1.0000
16.250 1.2044 0.08614 0.07864 -0.0200 0.0567 1.0000
16.500 1.2073 0.08922 0.08186 -0.0207 0.0549 1.0000
16.750 1.2098 0.09233 0.08506 -0.0215 0.0533 1.0000
17.000 1.2127 0.09534 0.08811 -0.0224 0.0518 1.0000
17.250 1.2171 0.09817 0.09098 -0.0230 0.0505 1.0000
17.500 1.2155 0.10216 0.09523 -0.0244 0.0494 1.0000
17.750 1.2130 0.10634 0.09961 -0.0260 0.0482 1.0000
18.000 1.2099 0.11064 0.10409 -0.0278 0.0471 1.0000
18.250 1.2068 0.11495 0.10855 -0.0297 0.0461 1.0000
18.500 1.2046 0.11911 0.11281 -0.0317 0.0451 1.0000
18.750 1.2054 0.12271 0.11648 -0.0334 0.0443 1.0000
19.000 1.2090 0.12577 0.11954 -0.0348 0.0433 1.0000
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Polar data table (+)
Polar graphs
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