NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il) Reynolds number: 50,000 Max Cl/Cd: 32.06 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc21010-il-50000.txt Download as CSV file: xf-sc21010-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-1010 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4401 0.10194 0.09448 -0.0159 0.9999 0.3453
-10.250 -0.4227 0.09799 0.09051 -0.0148 0.9999 0.3547
-10.000 -0.4254 0.09550 0.08810 -0.0133 0.9999 0.3642
-9.750 -0.4550 0.09567 0.08847 -0.0100 0.9999 0.3755
-9.500 -0.4294 0.09110 0.08382 -0.0092 0.9999 0.3879
-9.250 -0.5520 0.05894 0.05141 -0.0574 0.9999 0.1603
-9.000 -0.5313 0.05199 0.04398 -0.0640 0.9999 0.1540
-8.750 -0.5019 0.04558 0.03697 -0.0706 0.9999 0.1505
-8.500 -0.4673 0.04084 0.03153 -0.0760 0.9999 0.1539
-8.250 -0.4279 0.03681 0.02659 -0.0810 0.9999 0.1577
-8.000 -0.4010 0.03435 0.02414 -0.0818 0.9999 0.1642
-7.750 -0.3661 0.03195 0.02122 -0.0842 0.9999 0.1744
-7.500 -0.3370 0.03013 0.01931 -0.0849 0.9999 0.1856
-7.250 -0.3066 0.02851 0.01754 -0.0857 0.9999 0.2027
-7.000 -0.2780 0.02700 0.01612 -0.0859 0.9999 0.2240
-6.750 -0.2491 0.02564 0.01498 -0.0862 0.9999 0.2586
-6.500 -0.2156 0.02418 0.01404 -0.0875 0.9999 0.3312
-6.250 -0.1897 0.02371 0.01463 -0.0859 0.9999 0.4766
-6.000 -0.1828 0.02460 0.01588 -0.0790 0.9999 0.5617
-5.750 -0.1782 0.02550 0.01687 -0.0719 0.9999 0.6118
-5.500 -0.1737 0.02627 0.01766 -0.0649 0.9999 0.6513
-5.250 -0.1669 0.02685 0.01819 -0.0588 0.9999 0.6884
-5.000 -0.1616 0.02717 0.01849 -0.0525 0.9999 0.7194
-4.750 -0.1556 0.02728 0.01855 -0.0467 0.9999 0.7496
-4.500 -0.1480 0.02719 0.01841 -0.0415 0.9999 0.7808
-4.250 -0.1398 0.02691 0.01807 -0.0367 0.9999 0.8135
-4.000 -0.1296 0.02643 0.01751 -0.0327 0.9999 0.8478
-3.750 -0.1210 0.02561 0.01663 -0.0285 0.9999 0.8797
-3.500 -0.1097 0.02462 0.01558 -0.0254 0.9999 0.9120
-3.250 -0.0926 0.02362 0.01451 -0.0239 0.9999 0.9450
-3.000 -0.0655 0.02278 0.01362 -0.0249 0.9999 0.9803
-2.750 -0.0448 0.02232 0.01313 -0.0259 0.9999 1.0001
-2.500 -0.0062 0.02255 0.01324 -0.0306 0.9999 1.0001
-2.250 0.0337 0.02289 0.01347 -0.0352 0.9999 1.0001
-2.000 0.0735 0.02330 0.01380 -0.0397 0.9999 1.0001
-1.750 0.1127 0.02378 0.01423 -0.0440 0.9999 1.0001
-1.500 0.1510 0.02432 0.01473 -0.0479 0.9999 1.0001
-1.250 0.1883 0.02490 0.01530 -0.0516 0.9999 1.0001
-1.000 0.2243 0.02554 0.01595 -0.0550 0.9999 1.0001
-0.750 0.2592 0.02622 0.01667 -0.0582 0.9999 1.0001
-0.500 0.2929 0.02695 0.01745 -0.0610 0.9999 1.0001
-0.250 0.3254 0.02774 0.01832 -0.0637 0.9999 1.0001
0.000 0.3566 0.02859 0.01927 -0.0661 0.9999 1.0001
0.250 0.3867 0.02951 0.02030 -0.0684 0.9999 1.0001
0.500 0.4155 0.03050 0.02142 -0.0705 0.9999 1.0001
0.750 0.4431 0.03158 0.02267 -0.0724 0.9999 1.0001
1.000 0.4693 0.03277 0.02403 -0.0743 0.9999 1.0001
1.250 0.4940 0.03408 0.02553 -0.0760 0.9999 1.0001
1.500 0.5503 0.03555 0.02735 -0.0833 0.9822 1.0001
1.750 0.6975 0.03264 0.02522 -0.0985 0.8898 1.0001
2.000 0.7880 0.02458 0.01797 -0.0946 0.7592 1.0001
2.250 0.8210 0.02670 0.01612 -0.0867 0.2430 1.0001
2.500 0.8653 0.02906 0.01801 -0.0889 0.1984 1.0001
2.750 0.9111 0.03123 0.02006 -0.0913 0.1744 1.0001
3.000 0.9511 0.03356 0.02240 -0.0929 0.1595 1.0001
3.250 0.9876 0.03623 0.02521 -0.0940 0.1506 1.0001
3.500 1.0199 0.03876 0.02794 -0.0944 0.1429 1.0001
3.750 1.0492 0.04186 0.03130 -0.0946 0.1374 1.0001
4.000 1.0753 0.04509 0.03508 -0.0939 0.1357 1.0001
4.250 1.0972 0.04848 0.03900 -0.0928 0.1338 1.0001
4.500 1.1158 0.05203 0.04304 -0.0914 0.1318 1.0001
4.750 1.1305 0.05619 0.04775 -0.0898 0.1327 1.0001
5.000 1.1429 0.06092 0.05293 -0.0882 0.1357 1.0001
5.250 1.1589 0.06610 0.05833 -0.0874 0.1386 1.0001
5.500 1.1448 0.07206 0.06531 -0.0839 0.1497 1.0001
5.750 1.1633 0.07817 0.07141 -0.0839 0.1543 1.0001
6.000 0.8889 0.11860 0.11316 -0.1219 0.4113 1.0001
6.250 0.8999 0.12386 0.11842 -0.1227 0.4071 1.0001
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Polar data table (+)
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