SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD6080 (9.2%) (sd6080-il) Reynolds number: 100,000 Max Cl/Cd: 60.46 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd6080-il-100000-n5.txt Download as CSV file: xf-sd6080-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3487 0.09200 0.08748 -0.0407 1.0000 0.0495
-7.750 -0.3525 0.08905 0.08463 -0.0420 1.0000 0.0495
-7.500 -0.3572 0.08629 0.08197 -0.0426 1.0000 0.0495
-7.250 -0.3633 0.07877 0.07451 -0.0400 1.0000 0.0296
-7.000 -0.3520 0.07661 0.07234 -0.0386 0.9951 0.0281
-6.750 -0.3294 0.07128 0.06698 -0.0462 0.9844 0.0266
-6.500 -0.3038 0.06469 0.06032 -0.0562 0.9735 0.0256
-6.250 -0.2774 0.05801 0.05349 -0.0656 0.9625 0.0256
-6.000 -0.2510 0.05134 0.04660 -0.0734 0.9519 0.0253
-5.750 -0.2235 0.04495 0.03986 -0.0798 0.9426 0.0252
-5.500 -0.1982 0.03863 0.03301 -0.0841 0.9323 0.0243
-5.250 -0.1735 0.03278 0.02632 -0.0865 0.9221 0.0234
-5.000 -0.1449 0.02935 0.02229 -0.0879 0.9147 0.0234
-4.750 -0.1195 0.02687 0.01934 -0.0881 0.9051 0.0236
-4.500 -0.0918 0.02479 0.01685 -0.0884 0.8973 0.0241
-4.250 -0.0641 0.02309 0.01481 -0.0884 0.8890 0.0248
-4.000 -0.0367 0.02168 0.01313 -0.0882 0.8808 0.0261
-3.750 -0.0085 0.02060 0.01175 -0.0880 0.8732 0.0290
-3.500 0.0174 0.01953 0.01059 -0.0877 0.8646 0.0317
-3.250 0.0449 0.01858 0.00952 -0.0873 0.8574 0.0346
-3.000 0.0705 0.01775 0.00854 -0.0867 0.8484 0.0390
-2.750 0.0979 0.01699 0.00774 -0.0863 0.8417 0.0515
-2.500 0.1232 0.01628 0.00713 -0.0859 0.8325 0.0850
-2.250 0.1496 0.01558 0.00673 -0.0857 0.8257 0.1582
-2.000 0.1748 0.01501 0.00646 -0.0853 0.8168 0.2478
-1.750 0.2004 0.01442 0.00622 -0.0849 0.8097 0.3746
-1.500 0.2235 0.01380 0.00614 -0.0838 0.8013 0.5450
-1.250 0.2431 0.01313 0.00608 -0.0810 0.7942 0.7514
-1.000 0.2934 0.01268 0.00570 -0.0846 0.7871 1.0000
-0.750 0.3197 0.01274 0.00553 -0.0841 0.7796 1.0000
-0.500 0.3458 0.01283 0.00542 -0.0837 0.7711 1.0000
-0.250 0.3721 0.01293 0.00533 -0.0833 0.7632 1.0000
0.000 0.3985 0.01302 0.00525 -0.0829 0.7553 1.0000
0.250 0.4247 0.01314 0.00522 -0.0825 0.7470 1.0000
0.500 0.4515 0.01323 0.00517 -0.0821 0.7395 1.0000
0.750 0.4776 0.01337 0.00521 -0.0817 0.7307 1.0000
1.000 0.5046 0.01345 0.00517 -0.0813 0.7236 1.0000
1.250 0.5306 0.01361 0.00527 -0.0810 0.7143 1.0000
1.500 0.5573 0.01372 0.00528 -0.0806 0.7066 1.0000
1.750 0.5836 0.01386 0.00538 -0.0802 0.6974 1.0000
2.000 0.6099 0.01401 0.00547 -0.0799 0.6885 1.0000
2.250 0.6367 0.01412 0.00551 -0.0795 0.6800 1.0000
2.500 0.6625 0.01428 0.00568 -0.0791 0.6696 1.0000
2.750 0.6889 0.01442 0.00579 -0.0786 0.6599 1.0000
3.000 0.7154 0.01454 0.00587 -0.0782 0.6505 1.0000
3.250 0.7411 0.01471 0.00605 -0.0777 0.6391 1.0000
3.500 0.7670 0.01486 0.00624 -0.0773 0.6279 1.0000
3.750 0.7930 0.01501 0.00639 -0.0768 0.6167 1.0000
4.000 0.8190 0.01515 0.00652 -0.0763 0.6050 1.0000
4.250 0.8446 0.01531 0.00674 -0.0757 0.5921 1.0000
4.500 0.8698 0.01549 0.00695 -0.0752 0.5781 1.0000
4.750 0.8950 0.01568 0.00717 -0.0746 0.5636 1.0000
5.000 0.9200 0.01587 0.00740 -0.0740 0.5484 1.0000
5.250 0.9447 0.01608 0.00768 -0.0733 0.5319 1.0000
5.500 0.9690 0.01631 0.00798 -0.0726 0.5136 1.0000
5.750 0.9929 0.01657 0.00827 -0.0718 0.4941 1.0000
6.000 1.0164 0.01685 0.00858 -0.0710 0.4731 1.0000
6.250 1.0393 0.01719 0.00897 -0.0701 0.4495 1.0000
6.500 1.0615 0.01758 0.00937 -0.0692 0.4239 1.0000
6.750 1.0828 0.01804 0.00982 -0.0681 0.3961 1.0000
7.000 1.1031 0.01859 0.01033 -0.0670 0.3666 1.0000
7.250 1.1224 0.01923 0.01094 -0.0657 0.3360 1.0000
7.500 1.1405 0.01997 0.01161 -0.0644 0.3053 1.0000
7.750 1.1575 0.02079 0.01237 -0.0630 0.2756 1.0000
8.000 1.1738 0.02168 0.01320 -0.0615 0.2473 1.0000
8.250 1.1890 0.02264 0.01411 -0.0600 0.2198 1.0000
8.500 1.2025 0.02369 0.01511 -0.0584 0.1917 1.0000
8.750 1.2141 0.02486 0.01616 -0.0566 0.1625 1.0000
9.000 1.2243 0.02611 0.01727 -0.0548 0.1326 1.0000
9.250 1.2334 0.02741 0.01844 -0.0528 0.1062 1.0000
9.500 1.2404 0.02873 0.01969 -0.0506 0.0849 1.0000
9.750 1.2469 0.03015 0.02110 -0.0484 0.0684 1.0000
10.000 1.2511 0.03181 0.02278 -0.0462 0.0537 1.0000
10.250 1.2531 0.03374 0.02471 -0.0440 0.0432 1.0000
10.500 1.2539 0.03584 0.02684 -0.0420 0.0374 1.0000
10.750 1.2552 0.03799 0.02910 -0.0403 0.0330 1.0000
11.000 1.2541 0.04043 0.03159 -0.0387 0.0304 1.0000
11.250 1.2559 0.04272 0.03407 -0.0375 0.0279 1.0000
11.500 1.2571 0.04513 0.03663 -0.0365 0.0260 1.0000
11.750 1.2565 0.04783 0.03946 -0.0358 0.0249 1.0000
12.000 1.2543 0.05082 0.04257 -0.0351 0.0240 1.0000
12.250 1.2522 0.05391 0.04577 -0.0346 0.0234 1.0000
12.500 1.2528 0.05682 0.04891 -0.0342 0.0227 1.0000
12.750 1.2535 0.05984 0.05211 -0.0339 0.0222 1.0000
13.000 1.2540 0.06297 0.05543 -0.0336 0.0216 1.0000
13.250 1.2543 0.06623 0.05888 -0.0335 0.0211 1.0000
13.500 1.2544 0.06960 0.06243 -0.0336 0.0207 1.0000
13.750 1.2531 0.07323 0.06625 -0.0338 0.0203 1.0000
14.000 1.2504 0.07712 0.07032 -0.0345 0.0198 1.0000
14.250 1.2464 0.08130 0.07468 -0.0355 0.0194 1.0000
14.500 1.2412 0.08574 0.07928 -0.0368 0.0190 1.0000
14.750 1.2355 0.09045 0.08415 -0.0384 0.0187 1.0000
15.000 1.2290 0.09537 0.08923 -0.0402 0.0184 1.0000
15.250 1.2215 0.10066 0.09466 -0.0423 0.0181 1.0000
15.500 1.2107 0.10684 0.10103 -0.0453 0.0179 1.0000
15.750 1.1984 0.11362 0.10805 -0.0489 0.0179 1.0000
16.000 1.1842 0.12116 0.11581 -0.0532 0.0178 1.0000
16.250 1.1703 0.12896 0.12380 -0.0579 0.0179 1.0000
16.500 1.1550 0.13754 0.13258 -0.0633 0.0179 1.0000
16.750 1.1401 0.14649 0.14168 -0.0690 0.0180 1.0000
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Polar data table (+)
Polar graphs
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