SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD6080 (9.2%) (sd6080-il) Reynolds number: 50,000 Max Cl/Cd: 39.62 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd6080-il-50000-n5.txt Download as CSV file: xf-sd6080-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD6080 (9.2%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3346 0.09723 0.09077 -0.0330 1.0000 0.1065
-7.750 -0.3349 0.09442 0.08806 -0.0336 1.0000 0.1066
-7.500 -0.3395 0.08861 0.08228 -0.0367 1.0000 0.0596
-7.250 -0.3414 0.08570 0.07948 -0.0361 1.0000 0.0563
-6.750 -0.3614 0.07899 0.07298 -0.0403 1.0000 0.0487
-6.500 -0.3658 0.07670 0.07076 -0.0387 1.0000 0.0479
-6.250 -0.3710 0.07419 0.06832 -0.0377 1.0000 0.0470
-6.000 -0.3750 0.07144 0.06560 -0.0374 1.0000 0.0461
-5.750 -0.3699 0.06774 0.06186 -0.0395 0.9977 0.0450
-5.500 -0.3411 0.06161 0.05554 -0.0474 0.9881 0.0432
-5.250 -0.3110 0.05540 0.04901 -0.0548 0.9788 0.0419
-5.000 -0.2785 0.05001 0.04323 -0.0610 0.9707 0.0421
-4.750 -0.2467 0.04548 0.03824 -0.0657 0.9622 0.0432
-4.500 -0.2136 0.04132 0.03351 -0.0696 0.9544 0.0444
-4.250 -0.1786 0.03753 0.02909 -0.0728 0.9473 0.0452
-4.000 -0.1447 0.03435 0.02529 -0.0749 0.9400 0.0459
-3.750 -0.1088 0.03165 0.02194 -0.0768 0.9334 0.0473
-3.500 -0.0734 0.02950 0.01923 -0.0782 0.9268 0.0501
-3.250 -0.0405 0.02812 0.01768 -0.0795 0.9195 0.0569
-3.000 -0.0043 0.02656 0.01582 -0.0807 0.9136 0.0642
-2.750 0.0266 0.02553 0.01467 -0.0813 0.9055 0.0790
-2.500 0.0621 0.02444 0.01354 -0.0827 0.8994 0.1134
-2.250 0.0915 0.02342 0.01269 -0.0833 0.8908 0.1733
-2.000 0.1245 0.02221 0.01207 -0.0846 0.8845 0.3017
-1.750 0.1461 0.02111 0.01195 -0.0834 0.8757 0.5266
-1.500 0.1941 0.01986 0.01144 -0.0849 0.8717 1.0000
-1.250 0.2198 0.02008 0.01124 -0.0848 0.8615 1.0000
-1.000 0.2508 0.02025 0.01102 -0.0854 0.8536 1.0000
-0.750 0.2788 0.02046 0.01090 -0.0855 0.8446 1.0000
-0.500 0.3059 0.02070 0.01086 -0.0854 0.8354 1.0000
-0.250 0.3371 0.02086 0.01076 -0.0859 0.8280 1.0000
0.000 0.3616 0.02115 0.01086 -0.0855 0.8180 1.0000
0.250 0.3929 0.02130 0.01080 -0.0859 0.8110 1.0000
0.500 0.4171 0.02162 0.01097 -0.0854 0.8009 1.0000
0.750 0.4436 0.02188 0.01110 -0.0852 0.7921 1.0000
1.000 0.4722 0.02208 0.01116 -0.0851 0.7841 1.0000
1.250 0.4963 0.02243 0.01142 -0.0846 0.7741 1.0000
1.500 0.5272 0.02253 0.01142 -0.0847 0.7674 1.0000
1.750 0.5497 0.02293 0.01178 -0.0839 0.7565 1.0000
2.000 0.5751 0.02323 0.01204 -0.0835 0.7471 1.0000
2.250 0.6040 0.02337 0.01214 -0.0833 0.7391 1.0000
2.500 0.6270 0.02376 0.01252 -0.0825 0.7282 1.0000
2.750 0.6530 0.02401 0.01279 -0.0820 0.7187 1.0000
3.000 0.6811 0.02413 0.01291 -0.0816 0.7098 1.0000
3.250 0.7042 0.02450 0.01331 -0.0808 0.6982 1.0000
3.500 0.7291 0.02476 0.01362 -0.0801 0.6874 1.0000
3.750 0.7577 0.02481 0.01372 -0.0796 0.6780 1.0000
4.000 0.7823 0.02504 0.01402 -0.0787 0.6662 1.0000
4.250 0.8060 0.02533 0.01438 -0.0778 0.6536 1.0000
4.500 0.8303 0.02555 0.01469 -0.0769 0.6410 1.0000
4.750 0.8551 0.02573 0.01500 -0.0760 0.6281 1.0000
5.000 0.8801 0.02586 0.01523 -0.0750 0.6147 1.0000
5.250 0.9048 0.02599 0.01547 -0.0740 0.6005 1.0000
5.500 0.9289 0.02613 0.01577 -0.0729 0.5853 1.0000
5.750 0.9527 0.02626 0.01603 -0.0717 0.5691 1.0000
6.000 0.9764 0.02637 0.01627 -0.0705 0.5521 1.0000
6.250 1.0008 0.02642 0.01643 -0.0693 0.5345 1.0000
6.500 1.0219 0.02668 0.01687 -0.0678 0.5142 1.0000
6.750 1.0437 0.02687 0.01719 -0.0664 0.4929 1.0000
7.000 1.0641 0.02716 0.01759 -0.0648 0.4696 1.0000
7.250 1.0849 0.02742 0.01791 -0.0632 0.4451 1.0000
7.500 1.1034 0.02785 0.01846 -0.0615 0.4183 1.0000
7.750 1.1204 0.02844 0.01909 -0.0596 0.3902 1.0000
8.000 1.1358 0.02916 0.01983 -0.0577 0.3613 1.0000
8.250 1.1495 0.03006 0.02071 -0.0558 0.3326 1.0000
8.500 1.1613 0.03112 0.02177 -0.0537 0.3046 1.0000
8.750 1.1713 0.03234 0.02301 -0.0516 0.2779 1.0000
9.000 1.1795 0.03370 0.02436 -0.0495 0.2529 1.0000
9.250 1.1851 0.03517 0.02576 -0.0471 0.2309 1.0000
9.500 1.1890 0.03679 0.02744 -0.0448 0.2087 1.0000
9.750 1.1916 0.03858 0.02919 -0.0427 0.1896 1.0000
10.000 1.1937 0.04057 0.03124 -0.0408 0.1698 1.0000
10.250 1.1935 0.04279 0.03346 -0.0391 0.1514 1.0000
10.500 1.1906 0.04529 0.03588 -0.0377 0.1342 1.0000
10.750 1.1868 0.04807 0.03873 -0.0368 0.1152 1.0000
11.000 1.1827 0.05107 0.04176 -0.0362 0.0995 1.0000
11.250 1.1786 0.05433 0.04501 -0.0358 0.0860 1.0000
11.500 1.1762 0.05762 0.04837 -0.0353 0.0758 1.0000
11.750 1.1737 0.06107 0.05186 -0.0350 0.0679 1.0000
12.000 1.1717 0.06453 0.05538 -0.0348 0.0616 1.0000
12.250 1.1714 0.06801 0.05901 -0.0346 0.0561 1.0000
12.500 1.1704 0.07157 0.06270 -0.0347 0.0519 1.0000
12.750 1.1694 0.07514 0.06629 -0.0348 0.0489 1.0000
13.000 1.1714 0.07887 0.07037 -0.0347 0.0462 1.0000
13.250 1.1712 0.08287 0.07464 -0.0349 0.0442 1.0000
13.500 1.1693 0.08713 0.07913 -0.0356 0.0429 1.0000
13.750 1.1655 0.09169 0.08389 -0.0366 0.0418 1.0000
14.000 1.1608 0.09647 0.08884 -0.0380 0.0409 1.0000
14.250 1.1560 0.10138 0.09393 -0.0395 0.0401 1.0000
14.500 1.1466 0.10735 0.10005 -0.0419 0.0396 1.0000
14.750 1.1317 0.11471 0.10767 -0.0458 0.0395 1.0000
15.000 1.1155 0.12284 0.11598 -0.0504 0.0395 1.0000
15.250 1.0988 0.13157 0.12490 -0.0555 0.0397 1.0000
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Polar data table (+)
Polar graphs
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