SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD5060 (9.5%) (sd5060-il) Reynolds number: 100,000 Max Cl/Cd: 51.52 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd5060-il-100000.txt Download as CSV file: xf-sd5060-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SD5060 (9.5%)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4519 0.09682 0.09201 -0.0130 1.0000 0.1255
-8.500 -0.4482 0.09354 0.08876 -0.0143 1.0000 0.1299
-8.250 -0.4880 0.09107 0.08651 -0.0242 1.0000 0.1346
-8.000 -0.4619 0.08602 0.08144 -0.0204 1.0000 0.1368
-7.750 -0.4485 0.08274 0.07816 -0.0194 1.0000 0.1397
-7.500 -0.4485 0.07948 0.07496 -0.0207 1.0000 0.1434
-7.250 -0.5125 0.05375 0.04859 -0.0501 1.0000 0.0802
-7.000 -0.4948 0.05060 0.04563 -0.0486 1.0000 0.0763
-6.750 -0.5031 0.04058 0.03450 -0.0511 1.0000 0.0662
-6.500 -0.4934 0.03662 0.03025 -0.0501 1.0000 0.0653
-6.250 -0.4823 0.03318 0.02640 -0.0489 1.0000 0.0648
-6.000 -0.4689 0.03056 0.02323 -0.0473 1.0000 0.0660
-5.750 -0.4543 0.02792 0.02020 -0.0459 1.0000 0.0678
-5.500 -0.4375 0.02587 0.01797 -0.0446 1.0000 0.0698
-5.250 -0.4189 0.02418 0.01606 -0.0433 1.0000 0.0720
-5.000 -0.3993 0.02268 0.01434 -0.0419 1.0000 0.0752
-4.750 -0.3788 0.02137 0.01274 -0.0407 1.0000 0.0804
-4.500 -0.3592 0.02031 0.01176 -0.0396 1.0000 0.0888
-4.250 -0.3383 0.01915 0.01060 -0.0386 1.0000 0.1002
-4.000 -0.3172 0.01810 0.00966 -0.0376 1.0000 0.1278
-3.750 -0.2964 0.01751 0.00920 -0.0369 1.0000 0.1734
-3.500 -0.2761 0.01726 0.00903 -0.0362 1.0000 0.2121
-3.250 -0.2564 0.01719 0.00901 -0.0355 1.0000 0.2500
-3.000 -0.2359 0.01696 0.00880 -0.0348 1.0000 0.2817
-2.750 -0.1990 0.01667 0.00869 -0.0372 0.9942 0.3206
-2.500 -0.1574 0.01640 0.00857 -0.0403 0.9858 0.3685
-2.250 -0.1173 0.01611 0.00851 -0.0430 0.9772 0.4247
-2.000 -0.0744 0.01577 0.00853 -0.0461 0.9696 0.5029
-1.750 -0.0402 0.01537 0.00858 -0.0472 0.9597 0.6021
-1.500 -0.0081 0.01499 0.00872 -0.0471 0.9506 0.7386
-1.250 0.0592 0.01452 0.00861 -0.0530 0.9464 0.9937
-1.000 0.1072 0.01467 0.00847 -0.0575 0.9373 1.0000
-0.750 0.1585 0.01473 0.00833 -0.0622 0.9289 1.0000
-0.500 0.1978 0.01484 0.00827 -0.0645 0.9175 1.0000
-0.250 0.2376 0.01491 0.00823 -0.0668 0.9067 1.0000
0.000 0.2800 0.01490 0.00812 -0.0691 0.8970 1.0000
0.250 0.3128 0.01495 0.00808 -0.0697 0.8845 1.0000
0.500 0.3419 0.01502 0.00807 -0.0695 0.8710 1.0000
0.750 0.3697 0.01507 0.00807 -0.0689 0.8573 1.0000
1.000 0.3964 0.01510 0.00805 -0.0679 0.8433 1.0000
1.250 0.4222 0.01512 0.00801 -0.0668 0.8290 1.0000
1.500 0.4473 0.01511 0.00795 -0.0654 0.8144 1.0000
1.750 0.4720 0.01509 0.00789 -0.0639 0.7994 1.0000
2.000 0.4967 0.01505 0.00781 -0.0624 0.7840 1.0000
2.250 0.5213 0.01500 0.00773 -0.0608 0.7683 1.0000
2.500 0.5460 0.01494 0.00763 -0.0593 0.7522 1.0000
2.750 0.5710 0.01487 0.00753 -0.0577 0.7356 1.0000
3.000 0.5954 0.01486 0.00749 -0.0563 0.7167 1.0000
3.250 0.6201 0.01484 0.00745 -0.0549 0.6966 1.0000
3.500 0.6453 0.01478 0.00734 -0.0535 0.6769 1.0000
3.750 0.6699 0.01480 0.00735 -0.0522 0.6534 1.0000
4.000 0.6950 0.01480 0.00728 -0.0509 0.6300 1.0000
4.250 0.7196 0.01486 0.00729 -0.0496 0.6032 1.0000
4.500 0.7440 0.01497 0.00735 -0.0483 0.5734 1.0000
4.750 0.7680 0.01515 0.00746 -0.0471 0.5400 1.0000
5.000 0.7916 0.01542 0.00761 -0.0459 0.5027 1.0000
5.250 0.8145 0.01581 0.00785 -0.0447 0.4624 1.0000
5.500 0.8369 0.01634 0.00820 -0.0435 0.4207 1.0000
5.750 0.8588 0.01702 0.00863 -0.0423 0.3812 1.0000
6.000 0.8809 0.01779 0.00923 -0.0413 0.3440 1.0000
6.250 0.9030 0.01863 0.00989 -0.0404 0.3129 1.0000
6.500 0.9254 0.01953 0.01068 -0.0396 0.2866 1.0000
6.750 0.9482 0.02049 0.01145 -0.0389 0.2650 1.0000
7.000 0.9711 0.02142 0.01238 -0.0381 0.2449 1.0000
7.250 0.9941 0.02239 0.01333 -0.0374 0.2278 1.0000
7.500 1.0170 0.02339 0.01433 -0.0368 0.2122 1.0000
7.750 1.0399 0.02444 0.01540 -0.0361 0.1981 1.0000
8.000 1.0624 0.02553 0.01653 -0.0354 0.1848 1.0000
8.250 1.0846 0.02669 0.01773 -0.0347 0.1723 1.0000
8.500 1.1066 0.02791 0.01900 -0.0340 0.1604 1.0000
8.750 1.1287 0.02920 0.02024 -0.0334 0.1490 1.0000
9.000 1.1488 0.03035 0.02153 -0.0324 0.1379 1.0000
9.250 1.1675 0.03178 0.02320 -0.0313 0.1272 1.0000
9.500 1.1865 0.03343 0.02497 -0.0304 0.1175 1.0000
9.750 1.2062 0.03502 0.02652 -0.0297 0.1081 1.0000
10.000 1.2204 0.03649 0.02834 -0.0281 0.0994 1.0000
10.250 1.2348 0.03851 0.03055 -0.0268 0.0914 1.0000
10.500 1.2524 0.04009 0.03202 -0.0260 0.0835 1.0000
10.750 1.2576 0.04228 0.03474 -0.0237 0.0771 1.0000
11.000 1.2723 0.04422 0.03653 -0.0229 0.0703 1.0000
11.250 1.2702 0.04667 0.03956 -0.0202 0.0658 1.0000
11.500 1.2801 0.04805 0.04088 -0.0189 0.0605 1.0000
11.750 1.2753 0.05146 0.04461 -0.0167 0.0576 1.0000
12.000 1.2607 0.05458 0.04813 -0.0137 0.0560 1.0000
12.250 1.2449 0.05812 0.05200 -0.0117 0.0548 1.0000
12.500 1.2277 0.06202 0.05617 -0.0106 0.0538 1.0000
12.750 1.2073 0.06666 0.06108 -0.0107 0.0534 1.0000
13.000 1.1801 0.07260 0.06730 -0.0123 0.0538 1.0000
13.250 1.1484 0.07996 0.07493 -0.0157 0.0550 1.0000
13.500 1.1161 0.08842 0.08359 -0.0206 0.0561 1.0000
13.750 1.0855 0.09786 0.09317 -0.0265 0.0575 1.0000
14.000 1.0580 0.10790 0.10328 -0.0327 0.0586 1.0000
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Polar data table (+)
Polar graphs
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