NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il) Reynolds number: 100,000 Max Cl/Cd: 48.75 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc21010-il-100000.txt Download as CSV file: xf-sc21010-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4713 0.09711 0.09177 -0.0323 0.9999 0.1508
-11.000 -0.5097 0.09510 0.08994 -0.0333 0.9999 0.1569
-10.750 -0.5475 0.09193 0.08697 -0.0333 0.9999 0.1586
-10.500 -0.5041 0.08896 0.08389 -0.0292 0.9999 0.1624
-10.250 -0.5098 0.08690 0.08189 -0.0268 0.9999 0.1667
-10.000 -0.5999 0.05598 0.05009 -0.0640 0.9999 0.0964
-9.750 -0.5781 0.04536 0.03850 -0.0718 0.9999 0.0826
-9.500 -0.5525 0.04074 0.03342 -0.0751 0.9999 0.0825
-9.250 -0.5224 0.03634 0.02847 -0.0787 0.9999 0.0838
-9.000 -0.4926 0.03288 0.02464 -0.0811 0.9999 0.0849
-8.750 -0.4633 0.03048 0.02201 -0.0826 0.9999 0.0869
-8.500 -0.4348 0.02894 0.02029 -0.0837 0.9999 0.0914
-8.250 -0.4025 0.02734 0.01822 -0.0851 0.9999 0.0960
-8.000 -0.3713 0.02541 0.01617 -0.0865 0.9999 0.1006
-7.750 -0.3418 0.02442 0.01509 -0.0873 0.9999 0.1083
-7.500 -0.3109 0.02310 0.01371 -0.0882 0.9999 0.1155
-7.250 -0.2807 0.02236 0.01285 -0.0890 0.9999 0.1269
-7.000 -0.2495 0.02130 0.01195 -0.0900 0.9999 0.1412
-6.750 -0.2157 0.02028 0.01119 -0.0918 0.9999 0.1656
-6.500 -0.1747 0.01905 0.01040 -0.0954 0.9999 0.2249
-6.250 -0.1267 0.01775 0.01035 -0.1007 0.9999 0.4469
-6.000 -0.1014 0.01802 0.01078 -0.1001 0.9999 0.5244
-5.750 -0.0787 0.01843 0.01122 -0.0988 0.9999 0.5714
-5.500 -0.0590 0.01887 0.01171 -0.0967 0.9999 0.6031
-5.250 -0.0407 0.01932 0.01221 -0.0943 0.9999 0.6278
-5.000 -0.0228 0.01980 0.01271 -0.0919 0.9999 0.6511
-4.750 -0.0027 0.02022 0.01311 -0.0901 0.9999 0.6732
-4.500 0.0149 0.02063 0.01354 -0.0878 0.9999 0.6912
-4.250 0.0321 0.02104 0.01396 -0.0853 0.9999 0.7087
-4.000 0.0471 0.02146 0.01442 -0.0823 0.9999 0.7266
-3.750 0.0625 0.02184 0.01482 -0.0795 0.9999 0.7445
-3.500 0.0800 0.02215 0.01515 -0.0773 0.9999 0.7612
-3.250 0.0997 0.02240 0.01540 -0.0759 0.9999 0.7766
-3.000 0.1204 0.02264 0.01564 -0.0747 0.9999 0.7916
-2.750 0.1418 0.02285 0.01586 -0.0738 0.9999 0.8061
-2.500 0.1641 0.02306 0.01609 -0.0732 0.9999 0.8205
-2.250 0.1864 0.02327 0.01631 -0.0726 0.9999 0.8352
-2.000 0.2088 0.02346 0.01654 -0.0721 0.9999 0.8501
-1.750 0.2313 0.02364 0.01676 -0.0717 0.9999 0.8649
-1.500 0.2538 0.02383 0.01699 -0.0714 0.9999 0.8801
-1.250 0.2760 0.02400 0.01722 -0.0710 0.9999 0.8960
-1.000 0.2979 0.02418 0.01746 -0.0707 0.9999 0.9130
-0.750 0.3195 0.02437 0.01772 -0.0704 0.9999 0.9320
-0.500 0.3537 0.02438 0.01784 -0.0725 0.9907 0.9533
-0.250 0.3923 0.02432 0.01789 -0.0754 0.9737 0.9971
0.000 0.4571 0.02464 0.01832 -0.0832 0.9587 1.0001
0.250 0.5286 0.02399 0.01781 -0.0905 0.9320 1.0001
0.500 0.5976 0.02274 0.01675 -0.0965 0.9065 1.0001
0.750 0.6684 0.02050 0.01471 -0.1011 0.8784 1.0001
1.000 0.7290 0.01798 0.01242 -0.1034 0.8474 1.0001
1.250 0.7741 0.01588 0.01049 -0.1028 0.7953 1.0001
1.500 0.8002 0.01669 0.00871 -0.0979 0.3093 1.0001
1.750 0.8139 0.01949 0.01024 -0.0961 0.1633 1.0001
2.000 0.8387 0.02110 0.01158 -0.0958 0.1358 1.0001
2.250 0.8669 0.02257 0.01290 -0.0962 0.1198 1.0001
2.500 0.8983 0.02436 0.01444 -0.0971 0.1088 1.0001
2.750 0.9308 0.02559 0.01579 -0.0979 0.0998 1.0001
3.000 0.9659 0.02770 0.01778 -0.0994 0.0934 1.0001
3.250 0.9991 0.02929 0.01957 -0.1001 0.0879 1.0001
3.500 1.0309 0.03115 0.02143 -0.1010 0.0827 1.0001
3.750 1.0640 0.03434 0.02477 -0.1020 0.0802 1.0001
4.000 1.0918 0.03648 0.02737 -0.1015 0.0784 1.0001
4.250 1.1174 0.03886 0.03019 -0.1009 0.0758 1.0001
4.500 1.1411 0.04196 0.03375 -0.1000 0.0749 1.0001
4.750 1.1611 0.04581 0.03810 -0.0986 0.0758 1.0001
5.000 1.1782 0.05021 0.04293 -0.0971 0.0776 1.0001
5.250 1.1934 0.05513 0.04815 -0.0958 0.0794 1.0001
5.500 1.1126 0.05257 0.04704 -0.0776 0.0917 1.0001
6.000 1.1807 0.08939 0.08499 -0.0885 0.1699 1.0001
6.250 1.1011 0.09196 0.08814 -0.0842 0.1664 1.0001
6.500 1.0620 0.09754 0.09383 -0.0842 0.1642 1.0001
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Polar data table (+)
Polar graphs
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