NASA SC(2)-0710 AIRFOIL (sc20710-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0710 AIRFOIL (sc20710-il) Reynolds number: 200,000 Max Cl/Cd: 45.02 at α=0.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20710-il-200000-n5.txt Download as CSV file: xf-sc20710-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0710 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7054 0.08055 0.07637 -0.0449 1.0000 0.0230
-12.500 -0.7827 0.06129 0.05681 -0.0588 1.0000 0.0222
-12.250 -0.8175 0.05471 0.05001 -0.0611 1.0000 0.0221
-12.000 -0.8456 0.05042 0.04554 -0.0603 1.0000 0.0221
-11.750 -0.8713 0.04740 0.04237 -0.0575 1.0000 0.0222
-11.500 -0.8860 0.04383 0.03855 -0.0568 1.0000 0.0224
-11.250 -0.8913 0.04034 0.03472 -0.0566 1.0000 0.0227
-11.000 -0.8890 0.03708 0.03108 -0.0563 1.0000 0.0231
-10.750 -0.8800 0.03419 0.02779 -0.0561 1.0000 0.0234
-10.500 -0.8660 0.03175 0.02497 -0.0560 1.0000 0.0239
-10.250 -0.8489 0.02985 0.02284 -0.0559 1.0000 0.0243
-10.000 -0.8295 0.02853 0.02143 -0.0557 1.0000 0.0248
-9.750 -0.8088 0.02739 0.02019 -0.0557 1.0000 0.0254
-9.500 -0.7871 0.02628 0.01895 -0.0556 1.0000 0.0261
-9.250 -0.7647 0.02516 0.01769 -0.0556 1.0000 0.0270
-9.000 -0.7414 0.02413 0.01648 -0.0556 1.0000 0.0283
-8.750 -0.7175 0.02314 0.01530 -0.0556 1.0000 0.0296
-8.500 -0.6933 0.02226 0.01444 -0.0559 1.0000 0.0308
-8.250 -0.6683 0.02152 0.01365 -0.0561 1.0000 0.0321
-8.000 -0.6428 0.02076 0.01279 -0.0563 1.0000 0.0338
-7.750 -0.6166 0.02005 0.01196 -0.0565 1.0000 0.0355
-7.500 -0.5893 0.01930 0.01123 -0.0573 1.0000 0.0375
-7.250 -0.5620 0.01884 0.01074 -0.0578 1.0000 0.0402
-7.000 -0.5313 0.01837 0.01017 -0.0589 0.9993 0.0432
-6.750 -0.4986 0.01775 0.00960 -0.0607 0.9985 0.0466
-6.500 -0.4660 0.01735 0.00914 -0.0622 0.9975 0.0507
-6.250 -0.4326 0.01683 0.00864 -0.0640 0.9967 0.0551
-6.000 -0.3994 0.01646 0.00826 -0.0657 0.9958 0.0604
-5.750 -0.3651 0.01602 0.00781 -0.0676 0.9951 0.0661
-5.500 -0.3307 0.01568 0.00746 -0.0695 0.9943 0.0739
-5.250 -0.2962 0.01528 0.00713 -0.0714 0.9937 0.0835
-5.000 -0.2626 0.01495 0.00683 -0.0732 0.9928 0.0981
-4.750 -0.2283 0.01457 0.00657 -0.0751 0.9920 0.1215
-4.500 -0.1927 0.01414 0.00635 -0.0775 0.9915 0.1661
-4.250 -0.1535 0.01348 0.00611 -0.0810 0.9916 0.2595
-4.000 -0.1086 0.01254 0.00596 -0.0860 0.9931 0.4364
-3.750 -0.0759 0.01239 0.00638 -0.0871 0.9921 0.5687
-3.500 -0.0461 0.01253 0.00659 -0.0873 0.9901 0.6064
-3.250 -0.0148 0.01268 0.00674 -0.0880 0.9882 0.6299
-3.000 0.0159 0.01290 0.00698 -0.0884 0.9863 0.6499
-2.750 0.0468 0.01318 0.00727 -0.0888 0.9845 0.6675
-2.500 0.0758 0.01343 0.00754 -0.0888 0.9817 0.6816
-2.250 0.1046 0.01362 0.00774 -0.0888 0.9783 0.6910
-2.000 0.1345 0.01381 0.00795 -0.0891 0.9756 0.6983
-1.750 0.1663 0.01398 0.00814 -0.0897 0.9734 0.7054
-1.500 0.2021 0.01405 0.00821 -0.0914 0.9713 0.7117
-1.250 0.2284 0.01413 0.00834 -0.0908 0.9655 0.7152
-1.000 0.2657 0.01406 0.00830 -0.0926 0.9608 0.7190
-0.750 0.3041 0.01386 0.00814 -0.0946 0.9539 0.7230
-0.500 0.3579 0.01326 0.00754 -0.0995 0.9442 0.7266
-0.250 0.4028 0.01256 0.00690 -0.1019 0.9267 0.7281
0.250 0.4740 0.01181 0.00622 -0.1035 0.8784 0.7318
0.500 0.5127 0.01152 0.00592 -0.1050 0.8347 0.7342
0.750 0.5461 0.01213 0.00542 -0.1047 0.5938 0.7366
1.000 0.5619 0.01347 0.00579 -0.1025 0.3996 0.7397
1.500 0.6063 0.01520 0.00647 -0.1009 0.1790 0.7446
1.750 0.6302 0.01577 0.00681 -0.1002 0.1289 0.7467
2.000 0.6555 0.01623 0.00715 -0.0997 0.1035 0.7490
2.250 0.6818 0.01664 0.00751 -0.0994 0.0875 0.7514
2.500 0.7088 0.01704 0.00787 -0.0993 0.0767 0.7540
2.750 0.7362 0.01751 0.00827 -0.0994 0.0689 0.7568
3.000 0.7634 0.01788 0.00868 -0.0993 0.0629 0.7591
3.250 0.7878 0.01842 0.00919 -0.0986 0.0577 0.7607
3.500 0.8134 0.01882 0.00967 -0.0981 0.0535 0.7625
3.750 0.8386 0.01929 0.01013 -0.0976 0.0494 0.7646
4.000 0.8637 0.01984 0.01073 -0.0971 0.0460 0.7672
4.250 0.8898 0.02033 0.01126 -0.0968 0.0427 0.7700
4.500 0.9159 0.02095 0.01187 -0.0966 0.0402 0.7732
4.750 0.9405 0.02163 0.01262 -0.0959 0.0378 0.7754
5.000 0.9647 0.02221 0.01329 -0.0952 0.0354 0.7773
5.250 0.9888 0.02280 0.01390 -0.0946 0.0334 0.7793
5.500 1.0126 0.02368 0.01484 -0.0938 0.0318 0.7815
5.750 1.0371 0.02456 0.01585 -0.0932 0.0303 0.7838
6.000 1.0618 0.02546 0.01686 -0.0927 0.0290 0.7864
6.250 1.0867 0.02637 0.01783 -0.0923 0.0280 0.7892
6.500 1.1094 0.02733 0.01884 -0.0915 0.0271 0.7911
6.750 1.1315 0.02859 0.02025 -0.0905 0.0263 0.7929
7.000 1.1539 0.02985 0.02177 -0.0895 0.0254 0.7951
7.250 1.1756 0.03111 0.02326 -0.0885 0.0243 0.7976
7.500 1.1969 0.03232 0.02466 -0.0875 0.0235 0.8005
7.750 1.2177 0.03366 0.02617 -0.0866 0.0230 0.8034
8.000 1.2372 0.03497 0.02763 -0.0855 0.0225 0.8059
8.250 1.2545 0.03639 0.02920 -0.0840 0.0221 0.8078
8.500 1.2694 0.03832 0.03133 -0.0822 0.0218 0.8099
8.750 1.2795 0.04108 0.03458 -0.0798 0.0214 0.8124
9.000 1.2841 0.04443 0.03844 -0.0768 0.0211 0.8151
9.250 1.2816 0.04845 0.04299 -0.0732 0.0208 0.8178
9.500 1.2708 0.05301 0.04806 -0.0691 0.0206 0.8204
9.750 1.2491 0.05758 0.05307 -0.0640 0.0205 0.8222
10.000 1.2203 0.06218 0.05803 -0.0588 0.0204 0.8243
10.250 1.1868 0.06799 0.06419 -0.0556 0.0204 0.8263
10.500 1.1477 0.07549 0.07201 -0.0554 0.0205 0.8282
10.750 1.1027 0.08638 0.08319 -0.0609 0.0207 0.8298
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Polar data table (+)
Polar graphs
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